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Aerodynamics

A comparison of methods used in lifting surface theory

This is Research and Technology Organization (RTO) AGARD-R-583, dated June 1971. In this report linearised potential flow used to calculated values of the air forces on oscillating wings for selection of platforms, modes of oscillation, frequencies and airspeeds. Results from a number of different computer programs and methods are compared in the three regimes: subsonic, sonic, and supersonic. No attempt is made to assess which programs are the most accurate. A survey of the different methods is included indicating their main features and how they differ from each other. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (9.18 MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

A selection of experimental test cases for the validation of CFD codes, volume 1

This is Research and Technology Organization (RTO) AGARD-AR-303-VOL-1, dated August 1994. This report presents the results of a study by Working Group 14 of the AGARD Fluid Dynamics Panel. This group was formed to establish an accessible, detailed experimental data base for the validation of Computational Fluid Dynamics (CFD) codes. The thirty nine test cases that are documented cover the subsonic, transonic, and supersonic flow regimes and five classes of geometries. Included in the five classes of geometries are: two dimensional airfoils; three dimensional wings, designed for predominantly attached flow conditions; slender bodies, typical of missile type configurations; delta wings, characterized by a conical type of vortex flow; and complex configurations, either in a geometrical sense or because of complicated flow interactions. The report is presented in two volumes. Volume 1 provides a review of the theoretical and experimental requirements, a general introduction and summary of the test cases, and recommendations for the future. Volume 2 contains detailed information on the test cases. The relevant data of all test cases has been compiled on floppy disks, which can be obtained through National Centers. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (9.67MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

A selection of experimental test cases for the validation of CFD codes, volume 2

This is Research and Technology Organization (RTO) AGARD-AR-303-VOL-2, dated August 1994. This report presents the results of a study by Working Group 14 of the AGARD Fluid Dynamics Panel. The thirty nine test cases that are documented cover the subsonic, transonic, and supersonic flow regimes and five classes of geometries. Included in the five classes of geometries are: Two Dimensional Airfoils; Three Dimensional Wings, designed for predominantly attached flow conditions; Slender Bodies, typical of missile type configurations; Delta Wings, characterized by a conical type of vortex flow; and Complex Configurations, either in a geometrical sense or because of complicated flow interactions. The report is presented in two volumes. Volume 1 provides a review of the theoretical and experimental requirements, a general introduction, summary of the test cases and recommendations for the future. Volume 2 contains detailed information on the test cases. Relevant data has been compiled on floppy disks. For individual titles, see N95-17847 through N95-17885. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (156.77MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Active control technology Applications and Lessons Learned

This is Research and Technology Organization (RTO) AGARD-CP-560 , dated January 1995. In the last decade, Active Control Technology (ACT) has emerged from the realm of theory and modest experimental applications to full-scale use on production aircraft, while more elaborate forms of ACT are under test for the future production of aircraft. New technologies have been applied in military fighters to maximize maneuverability and agility, and in civil transports to reduce trim drag, lower pilot workload and improve riding qualities. During this symposium the status of Active Control Technology was assessed in light of the experience gained over the last decade. The symposium was organized around four sessions comprising 28 technical papers in all. These sessions focused on: Specifications for flight control design, Design and analysis methods, System integration and Implementation of experience. For individual titles, see N95-31990 through N95-32017. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (104MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Active Control Technology for Enhanced Performance Operational Capabilities of Military Aircraft, Land Vehicles and Sea Vehicles

This site provides access to a Research and Technology Organization Meeting Proceedings, RTO-MP-051, Paris, June 2001. The document contains papers presented at the Symposium of the RTO Applied Vehicle Technology Panel (AVT) held in Braunschweig, Germany, 8-11 May 2000. The Symposium analysed the potential of active control technology for the performance demands of future vehicles and engines, in particular high manoeuvrability, lower specific fuel consumption, higher power-to-weight ratios and lower life-cycle cost. Performance, stability, control, fluid dynamics, structural and engine layout questions were dealt with in 5 keynotes and 77 papers. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (126Mbytes) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Advanced Aerodynamic Measurement Technology

This is Research and Technology Organization(RTO) AGARD Conference Proceedings, AGARD-CP-601, dated May 1998. This proceedings was sponsored by the Advisory Group for Aerospace Research and Development. The papers prepared for the AGARD Fluid Dynamics Panel (FDP) Symposium, "Advanced Aerodynamic Measurement Technology" are contained in this report. In addition, a Technical Evaluator's Report aimed at assessing the success of the Symposium in meeting its objectives, and an edited transcript of the General Discussion held at the end of the Symposium are also included. Measurement techniques were presented for flows from subsonic to hypersonic Mach numbers and environments from cryogenic to high-enthalpy reacting flows. Papers presented during the sessions addressed the following subjects: Particle Image Velocimetry; Doppler Global Velocimetry; Molecular Diagnostic Techniques; Holographic Interferometry; Skin Friction Measurements; Pressure Sensitive Paints; and Balance and Model Deformation Measurements. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text of the document (152 Mb) can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Advanced Technologies Incorporated

This company provides aerospace research and development products and engineering and fabrication services such as wind tunnels, test equipment, prototype hardware and experimental helicopters. The site provides background information to the company and information on its product range with supporting images.

AEgis Simulation Inc. - ACSL (Advanced Continuous Simulation Language) Software

ACSL (Advanced Continuous Simulation Language) products are owned by AEgis Software. Aerospace and defence applications of ACSL software products include: simulation of fixed and rotary wing flight dynamics; missile simulation, marine propulsion system simulation; and simulation of spacecraft dynamics. The site provides access to a range of information resources including: a product overview, a description of industry applications, and details of ACSL training programmes. The publications section provides access to a collection of papers in the ACSL electronic library. These cover many topic areas such as: aeronautics, aircraft design, aerodynamics, unmanned aircraft, engines, flight simulations, and vehicle dynamics. The full-text papers seem to be available in a variety of formats including HTML and PDF.

Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment

This web site provides access to a NATO Research and Technology Organization (RTO) document titled: Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment, proceedings of the symposium of the RTO Applied Vehicle Technology Panel (AVT), held in Ottawa, Canada, 18-21 October 1999, RTO-MP-035, June 2000. The objective of the symposium was to survey the current and future scene, given the trend in industry towards a more concurrent and multi-disciplinary approach to aerospace vehicle engineering. The symposium included thirty two papers and a keynote address, and these were organised into a keynote session and five others covering the following topics: the role of aerodynamics in concept phase of a project design; MDO and the aerodynamics design process; methodologies/tools for aerodynamic optimisation; application of methodologies/tools for aerodynamic optimisation; and techniques for rapid database generation. Citation and abstract details are in HTML, table of contents in PDF format, and the full text is available online, also in PDF format (51 Mbytes).

Aerodynamic Engine/Airframe Integration for High Performance Aircraft and Missiles

This is Research and Technology Organization (RTO) AGARD-CP-498, dated September 1992. The objective of the symposium was to review the state-of-the-art in aerodynamic engine/airframe integration techniques and to report on the progress which has been achieved during engineering project work in recent years. Because the treatment of this subject requires an interdisciplinary approach, both experimentalists and theoreticians were invited to contribute to the meeting. Six sessions were organized to cover the essential subdisciplines requiring aerodynamic engine/airframe integration during the concept-assessment and design phases for new aerospace vehicles. For individual titles, see N93-13200 through N93-13231. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (** MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Aerodynamic interference

This is Research and Technology Organization (RTO) AGARD-CP-71, dated January 1971. The purpose of this Specialist Meeting was t o survey a number of the more important aspects relating t o aerodynamic interference and thereby to provide an understanding of the basic sciences involved, the techniques presently employed and the results of the most recent work in NATO countries. The three-day meeting was arranged as follows with each Session chaired by a member of the Programme Committee: 1. Classical aspects of interference, configuration studies of lift, drag, and high angle of attack characteristics. session I: Wing-Body, and Session 11: Wing-Body-Tail. 2. Airframe-propulsion interference for both commercial and military high performance aircraft. Session 111: Military, and Session IV: Commercial Transport. 3. Aerodynamics dealing with the properties and characteristics of forces and moments exerted on objects in motion and in the vicinity of other shapes. Airframe Stores. This discussion was a very valuable exercise in surveying some of the results presented in this meeting and follows the papers presented in this publication. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (85.5MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Aerodynamic Measurement Technology (AMT) Technical Committee

This is the home page of this AIAA (American Institute of Aeronautics and Astronautics) technical committee. The site includes background information to the committee such as its scope, charter, names of members and their interests, minutes of the committee meetings, details of papers to be presented at future conferences and descriptions of AMT techniques along with references (or links to references) for more information. This glossary is not intended to be a complete source, but rather a starting place for some of the modern diagnostic techniques.

Aerodynamics and Acoustics of Propellers

This is Research and Technology Organization (RTO) AGARD-CP-366, dated February 1985. A state of the art review of the aerodynamic design and testing of modern propellers, acoustic and vibration environmental problems and their solutions, and considerations in the integration of the propeller(s) and airframe is presented. Propellers have recently become a focus of attention after having been neglected for many years. The efficient use of propellers as a propulsion medium up to Mach 0.6 was realized at the expense of high noise and vibration. Since the mid-1970s there have been many developments, including the propfan, with an aerodynamic efficiency of 80% at Mach 0.8 now seriously challenges the fanjet. The advent of the supercritical airfoil is another significant development beginning to influence propeller design. For individual titles see N86-11148 through N86-11176. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (66.77MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Aerodynamics for Students

This is a Web textbook about aerodynamics aimed primarily at undergraduate level. It has been written by D. J. Auld of the faculty of Aerospace, Mechanical and Mechatronic Engineering at the University of Sydney, Australia and is intended primarily for their use. The contents are broken down into 8 main topics, namely fluid mechanics, aerodynamics, gas dynamics, aircraft performance, propulsion, datasheets, assignments and resources and a data library of wind tunnel experimental data.

Aerodynamics of Bicycles

This is a brief tutorial about the aerodynamics of bicycles. It has been co-written by A. J. Smits and B. S. H. Royce of the Gas Dynamics Laboratory, Department of Mechanical and Aerospace Engineering at Princeton University. The tutorial covers topics such as wind speeds and directions, the characteristics of fluids, pressure, streamlining, transition and turbulence, separation, drag, lift and stall. Please note that some of the "useful links" at the bottom of the tutorial are broken.

Aerodynamics of Store Integration and Separation

This is Research and Technology Organization(RTO) AGARD Conference Proceedings, AGARD-CP-570, dated February 1996. The papers prepared for the AGARD Fluid Dynamics Panel (FDP) Symposium on 'Aerodynamics of Store Integration and Separation', which was held 24-27 April 1995 in Ankara, Turkey are contained in this report. The aim of this symposium was to bring together engineers in the fields of theoretical and experimental aerodynamics, as applied to the store integration problem, to review and discuss the state of the art in the prediction, methodology and experimental techniques currently being developed and applied to the aerodynamics of store carriage and release and to assess new design concepts. For individual titles, see N96-25348 through N96-25369. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text of the document (113 Mb) can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

AeroInfo

AeroInfo is a searchable and browsable aerospace information directory, produced by the Information Center for Aerospace Science and Technology (ICAST) at the National Aerospace Laboratories in Bangalore. It covers most fields of aerospace including aeronautics, aviation, aerodynamics, CFD, avionics, composites, mechanical engineering, materials science, and computer science. There is also a section on worldwide aerospace agencies and a searchable database of papers, journals, technical reports, standards, patents and regulatory information.

Aeronautics Learning Laboratory for Science Technology and Research

This educational website includes material on the history of aeronautics, principles of aeronautics and aerospace education and careers at three different levels: Level 1 - for middle/junior high school students; Level 2 - for junior high/high school students and Level 3 - for high school/lower division college students. A teachers guide is available along with information on research projects, relevant links and a photo gallery. There is also information on how to obtain the teaching material on a CD-ROM.

Aircraft Optimization for Minimal Environmental Impact

This document is a dissertation submitted to the department of aeronautics and astronautics and the committee on graduate studies of Stanford University in partial fulfillment of the requirements for the degree of doctor of philosophy in 2004 by Nicolas Eugene Antoine. This research explores the feasibility of integrating noise and emissions as optimization objectives at the aircraft conceptual design stage, thereby allowing a quantitative analysis of the trade-offs between environmental performance and operating cost. Beyond meeting regulations and establishing environmental performance trades, the design tool allows the generation of extremely low-noise and low-emissions designs that could, in the future, dramatically decrease the environmental impact of commercial aviation, albeit at the expense of increased operating cost. To these ends, a preliminary design tool was developed that uses a multi-objective genetic algorithm to determine optimal aircraft configurations and to estimate the sensitivities between the conflicting objectives of low noise, low emissions, and operating costs. The design tool incorporates ANOPP, a detailed noise prediction code developed at NASA Langley, and NASA Glenn’s NEPP engine simulator, as well as aircraft design, analysis, and optimization modules developed at Stanford University.

Aircraft Weapon System Compatibility and Integration

This web site provides access to a Research and Technology Organization Meeting Proceedings, RTO-MP-016, Paris, April 1999. The documents contains papers presented at the RTO Systems Concepts and Integration Panel (SCI) Symposium held in Chester, United Kingdom, 28-30 September 1998. The objectives of the symposium were to review the overall state-of-the-art in aircraft weapon system compatibility and integration and to inform possible paths for future development. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (29 Mbytes) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library

American Institute of Aeronautics and Astronautics (AIAA) Home Page

The AIAA is a US-based organisation and is a professional society with the aim of progressing engineering and science within aviation, space and defence. This large site provides background information about the AIAA, a calendar of events, information on professional development courses and full text journal articles and technical meeting papers (for subscribers only). In addition there is a searchable database of meeting papers which is available free of charge, details of membership benefits and activities, and educational programmes. The site is searchable.

Application of Direct and Large Eddy Simulation to Transition and Turbulence

This is Research and Technology Organization (RTO) AGARD-CP-551 , dated December 1994. The papers prepared for the AGARD Fluid Dynamics Panel (FDP) Symposium on 'Application of Direct and Large Eddy Simulation to Transition and Turbulence', which was held April 1994 in Greece are contained in this report. In addition, a Technical Evaluator's Report assessing the success of the Symposium objectives, and an edited transcript of the General Discussion are also included. In the past two decades significant progress has been made in the numerical simulation of turbulent flows. Vast improvements in speed and memory size of modern supercomputers, and recent progress in simulation algorithms and parallel computation have put us on the threshold of being able to simulate flows in configurations of engineering interest. For individual titles, see N95-21062 through N95-21098. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (114.43MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Applied Aerodynamics : A Digital Textbook : Demonstration Version

This site provides a demonstration version of this text dated August 1997. It was developed for a course in applied aerodynamics at Stanford University by Ilan Kroo, a professor in aeronautics and astronautics at Stanford. Several chapters that appear in the released version are not present. The textbook is available in HTML format. Topics covered include fluid fundamentals, 2D potential flow, airfoils, 2D and 3D compressibility, boundary layers, 3D potential flow, 3D viscosity, wing design and configuration aerodynamics.

Appraisal of the Suitability of Turbulence Models in Flow Calculations

This is Research and Technology Organization (RTO) AGARD-AR-291, dated July 1991. A status review is presented of the activities in several NATO nations which is aimed at assessing the use and suitability of existing, and emerging, turbulence models in flow field calculations. Assessments are presented for both steady and unsteady flow fields associated with a variety of problems. These problems included forced convection flow fields for both attached and separated shear layers, two phase flow, and turbulent reacting flows in addition to flow fields driven by free convection. These assessments indicate that there is presently no universal turbulence model which provides acceptable results for a broad spectrum of flow problems and some doubt is expressed concerning the possibility of ever being able to develop such a model. However, some success is noted for turbulence models which were developed for and applied to problems with similar flow field characteristics. For individual titles, see N91-32444 through N91-32451. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (21.59MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Arnold Engineering Development Center

The Arnold Engineering Development Center (AEDC) is an aerospace ground test and evaluation/simulation centre. The site provides a description of the AEDC testing facilities and competencies in the following: aerodyamics/wind tunnels, propulsion systems, hypersonics, rockets, space systems, computational modeling and instrumentation. Each section includes a test highlights fact sheet.

Assessment of lift augmentation devices

This is Research and Technology Organization (RTO) AGARD-LS-43, dated February 1971. This publication contains edited versions of the lecture notes and complementary discussions from the AGARD - VKI Lecture Series on “Assessment of Lift Augmentation Devices”, at the von Karman Institute for Fluid Dynamics during the week 20-24 April 1970. The lecture series was designed to provide an up-to-date account of special aerodynamic problems and applications of lift-augmentation devices; including appraisals of the present state of knowledge, novel aerodynamic advances, experimental and theoretical treatments, applications for transport and combat aircraft, important areas for research and development. It was primarily intended for aeronautical engineers with a need to acquire a more adequate background on lift-augmentation devices. But short discussions were held after most of the lectures, together with a final Discussion Seminar, to take advantage of participants with specialised knowledge’ as appropriate. The Course was well supported as regards both the number of attendees (about 100) and their technical quality. The organisation was carried out under the auspices and with the support of AGARD, in collaboration with the von Karman Institute who had the responsibility for the general administration and local organisation. A special tribute must be paid to the lecture staff, for the quality of their presentations, the valuable analysis contained in their lecture notes provided for distribution during the Course, and their cooperative participation in discussions. Our thanks also go to the official and private organisations through whose courtesy it was possible to offer such technical experts as lecturers. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (32.73MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Association of European Research Establishments in Aeronautics (EREA)

EREA is a non-profit association comprising a number of leading european aerospace research organisations. Founded in October 1994 EREA's mission is is to provide European industry and authorities as well as governments with a cost effective high quality aeronautics technology base through joint research programmes and through the harmonised use of resources, facilities and personnel exchange. The site contains mainly descriptive information covering the Association's founding, history and development, its mission, objectives and vision, organisation and capabilities. Other sections of the site provide news and spin-offs, including brief examples of how aeronautical research disseminates technology to other sectors.

Beginner's Guide to Aerodynamics

This site is produced by the NASA Glenn Research Center as part of their Learning Technologies Project (LTP) to provide introductory information about aerodynamics to support school teachers' maths and science lessons. Each topic addressed is accompanied by a slide and explanatory text. Problems for students to work on are also provided. Subjects covered include basic aerodynamics problems, Newton's laws, static gases, moving gases, the atmosphere, forces, and aeroplane parts and motion.

Blended Wing Body : Design Challenges for the 21st Century

This provides access to the text and slides of a presentation made by Al Bowers, who is a Senior Aerodynamicist at NASA's Dryden Flight Research Center. The presentation was prepared for a The Wing is The Thing (TWITT) meeting, held at Dryden on September 16th 2000. The text is available in HTML format and the slides actual slides (jpgs) range in size from 49k to 104k, the average being about 60k. This presentation available from The Wing is The Thing web site.

Central Aerohydrodynamic Institute (TsAGI)

The site provides information about one of the key Russian state aerospace research centers. Information on the site is arranged under a number of activity areas including; aerodynamics, flight dynamics, strength, hydrodynamics, measuements, and non-aerospace activities. The site provides general information about the Institute including a brief history and image gallery. The Institute's test facilities are described, a list of staff publications and news and contacts sections.

CFD Research Corporation (CFDRC)

The company is involved in the development of engineering simulations software, innovative designs and prototyping. Its products include advanced computational fluid dynamics and multiphysics software for simulations of fluid, thermal, chemical, biological, electrical and mechanical phenomena. CFDRC also produces CFD-FASTRAN, a compressible flow solver specially designed for aerodynamic and aerothermodynamic applications. The web site includes corporate information, including a patents portfolio, descriptions of software and services, details of application areas such as aircraft aerodynamics, aerothermodynamics, aeroelasticity, crew escape systems, flow control, stores separation, combustion, propulsion, and Micro / Nano Electronics. Other sections of the site cover news and events, and careers information.

CFD Zone

This site has been created by NASA Langley in order to introduce the ways that NASA uses computers to simulate aerodynamic problems (computational fluid dynamics). The site contains information on the following topics - history, equations, simulation, grid generation, and examples of simulated flow phenomena. Users are requested to log in using a unique identifier, but no password is required.

Collectives and Complex System Design

This report is part of VKI lecture series on Optimization Methods & Tools for Multicriteria/Multidisciplinary Design, created November 15-19, 2004 by I. Kroo Stanford University, U.S.A. This paper deals with two aspects of collective design: the application of optimization in the design of collectives, and the use of collectives for engineering design itself, in which multiple individuals or teams design parts of a large-scale system. A collective is a group of self-motivated agents that maximize system performance through the pursuit of local objectives. Examples are drawn from aeronautical engineering, where well-developed models in the many relevant disciplines may be used to analyze and optimize the complete system. The design of aircraft, involving many individuals or organizations, and the formation flight of geese, for example, share many similar features. In each case, individuals must decide on a course of action that must benefit the system as a whole, despite the requirement that they act locally and cannot immediately ascertain the effect of their actions on the entire system. Examples demonstrate how multi-level distributed optimization can be used to achieve optimal system performance while focusing on local degrees of freedom and how a similar approach leads to the optimal V-shaped flock of geese, even when individual birds seek only to maximize their own local goals. Additional applications of these ideas show how collectives may provide new engineering solutions to problems in aerospace design.

Compressible Aerodynamics Calculator

This facility allows you to calculate the standard relations for the compressible flow of a perfect gas. Three sets of relations are included - isentropic flow relations, normal shock relations and oblique shock relations. These have all been taken from standard aerodynamics texts. The calculator has been written by William Devenport at the Aerospace and Ocean Engineering Department of the Virginia Tech in the U.S.

Cranfield University Aerospace

Cranfield has been at the forefront of the development of aerospace technology for 60 years and is one of the largest academic centres in western Europe for strategic applied research, development and design. Cranfield University Aerospace brings together the University’s aerospace capabilities from all its five Schools into areas of strategic importance for its clients, within the aerospace and aviation markets. It consists of the following technology areas: flow control and prediction, computer integrated design, air transport management, human factors, avionics and simulation, structures and materials, air vehicle technology, flight test and dynamics and astronautics and space engineering. The site details Cranfield University Aerospace's capabilities, courses and current projects.

Delft Aerospace

This is the web site of the Faculty of Aerospace Engineering, Delft University. It describes the various educational programmes on offer along with supporting course information. There is also information on the various research groups, facilities, support services, student organisations as well as the Delft Aerospace Alumni Society. Other sections of the site include news and events, and a database of staff contact information.

Delphion Patent Search Form

This site allows you to search for United States patents, European patents and patent applications, Patent Cooperation Treaty (PCT) application data from the World Intellectual Property Office, the Patent Abstracts of Japan and INPADOC data. The service can be searched in several different ways, including patent number, US classification and Boolean keyword search. It is possible to view to the bibliographic information of granted US patents free of charge, all other services are payable. You will need to register to use this service, which is free of charge.

Department of Aeronautics and Astronautics at the University of Southampton

The Department of Aeronautics and Astronautics at the University of Southampton is a member of the School of Engineering Sciences. The department name reflects the international reputation of Southampton in both Aeronautics & Astronautics and encompasses a broad range of disciplines within the field of aerospace engineering with applications to the specification, design and construction of airframes, engines, satellites and other spacecraft. These disciplines include aerodynamics, flight mechanics, materials, propulsion, structures, as well as aircraft and spacecraft systems. Cutting-edge research into all these disciplines is carried out within the School of Engineering Sciences by recognised experts in their specific fields. The web site gives information about the department, staff, research interests, the undergraduate and postgraduate courses available, facilities, including a wind tunnel complex which ranges from low speed to hypersonic, as well as the Department's links with industry and government research laboratories.

Department of Aerospace and Ocean Engineering at Virginia Tech

The Department Aerospace and Ocean Engineering at Virginia Tech makes use of the World Wide Web to distribute and provide teaching materials. These materials are catalogued by course. The site provides access to teaching materials, including lecture notes, tutorials, assignments, and homework for a range of courses. There are also Java and Javascript programs, self-taught units, course texts, manuals, homeworks and handouts in HTML, PostScript and PDF formats, and computer programs. The site also contains descriptive information about the Department's research activities including its facilities, research interests and research groups.

Department of Aerospace Engineering at the University of Bristol

Part of the Faculty of Engineering, the Department of Aerospace Engineering at the University of Bristol has research interests in the areas of fluid flow and aerodynamics, thermo-fluid dynamics, dynamics and control systems, structures and materials, and space engineering. The site contains a description of the research activities of the department and information about staff, as well as available courses. The site also provide access to an article written by Sir Robert Wall which looks back over the University�s contribution to the first 100 years of manned flight.

Design Loads for Future Aircraft

This site provides access to a Research and Technology Organization (RTO) Technical Report, RTO-TR-045, published in February 2002. The report addresses the requirements for design loads on the structure of future NATO aircraft imposed by regular flight and manoeuvring. Load critical flight manoeuvres and external loads such as those caused by turbulence are considered, as are aspects such as metal and composite structures and operational aspects. Some actual failure cases are analysed. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text of the document (4.21 Mbytes) can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Last updated: 02/07/2002.

Determination of Absolute Levels from Phased Array Measurements Using Spatial Source Coherence

This technical report (NLR-TP-2002-226) was published by NLR (the National Aerospace Laboratory of the Netherlands) in 2002 and was written by S. Oerlemans and P. Sijtsma. The phased array technique is a valuable tool in acoustic testing for its capability to distinguish between different source locations. However, the interpretation of phased array measurements is still difficult due to the simultaneous occurrence of several effects: the size and level of a spot in a conventional acoustic 'source plot' may be affected by a combination of (1) the limited resolution of the array (2) coherence loss during propagation to the array (3) the spatial extent of the source region. This ambiguity complicates the determination of absolute source levels from phased array measurements. The current paper addresses this problem for a noise source that is extended mainly in one direction, i.e. trailing-edge noise. Simulations are done for a line source, and the influence of array resolution and source coherence length on the array output is investigated. Furthermore, an array processing technique is presented which determines the coherence level between different sources in the scan plane. As a first application, the technique is used to identify mirror sources in a closed wind tunnel. The new method is then applied to trailing-edge noise measurements in NLR's Small Anechoic Wind Tunnel, in order to estimate the spanwise coherence length. In conjunction with the simulations this enables an improved determination of absolute trailing-edge noise from phased array measurements. [Taken from abstract]. The full text is available as a PDF file.

DLR Publications

The DLR is the German space agency. It plans Germany's space activities, carries out space-flight programmes and activities and represents its space community's interests. This service provides the facility to search its publications in both German and English. It is possible to search by keyword and/or author, restrict by department within the DLR, document type, or by year back to 1990. Bibliographic information only is available.

Dryden Aircraft Movie Collection

This collection contains short digitized video clips of many of the unique research aircraft flown at NASA Dryden Flight Research Center from the 1940s to the present. No copyright protection is asserted for these movies. The movies can be viewed with Quicktime. The films are listed in alphabetical order according to aircraft name and the research programme they are associated with is given.

Dryden Technical Reports Server (DTRS)

This service is available to search as part of the NASA Technical Reports Server, or on its own from this site. It is possible to search for and view details of reports, and view the full text of reports in PDF format from this service. Reports are available back to 1947 and up to the present day.

Effect of Residual and Intercycle Ice Accretions on Airfoil Performance : Final Report

This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-02/68, by Andy P. Broeren and Michael B. Bragg, dated May 2002. This report describes the results of an experimental study designed to characterize and evaluate the aerodynamic performance penalties of residual and intercycle ice accretions that result from the cyclic operation of a typical aircraft deicing system. The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library.

Effects of Extreme Winds on Structures

This report from the US National Research Council is available in full text in HTML format from the National Academy Press. The report assesses the suitability of a proposal to create a large-scale wind test facility (LSWTF) in order to enhance understanding of how extreme winds such as tornadoes and hurricanes impact on light-frame structures. The committee concluded that a LSWTF should not be constructed for both technical and economic reasons.

Eng-Tips Forums : Aeronautic Engineers

This is a mailing list service or 'Web community' designed for engineers to make contact and discuss issues and problems. It is free of charge and the forums can be browsed and messages read without registration. However, if you wish to post a message you must register. The service has more functionality for registered members, including searching and the 'personal profile' facility which allows engineers to tell others something about themselves. The 'Aeronautic engineers' section includes forums devoted to aircraft engineering, aerodynamic engineering and rotorcraft engineering.

Engine-airplane interference and wall corrections in transonic wind tunnel tests

This is Research and Technology Organization (RTO) AGARD-AR-36 , dated August 1971. Recent developments of high performance airplanes have generated requirements for the prediction of the aerodynamic performance of airplane designs with extremely high accuracy, certainly better than that which is presently possible with available experimental techniques. As a result, a critical review of present experimental methods is taking place, and development of new experimental techniques is in progress. Such activity is primarily carried on at a national level; however, substantial activity in this field exists to some degree in several of the NATO nations. This report is consisted of three parts, first is the operation of the committee and list of participants with conclusion and recommendations. Second is the engine airplane interference in transonic test, which is a compilation of the response to a distributed questionnaire on engine-frame interference in transonic tests among aeronautical laboratories operating transonic wind tunnels, aircraft manufacturers, engine companies and airplane users in the AGARD countries. Finally, the third part is the wall corrections for airplanes with lift in transonic wind tunnel test which summarizes the technical information supplied as written contributions or in oral discussions by the members of the Ad Hoc Committee. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (39.03MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

ESDU International

ESDU create and maintain over 22 series of validated engineering design data covering structural, mechanical, aeronautical and chemical process engineering. They are produced by committees of independent experts who ensure that each Data Item is a sound technical document which presents a clear explanation of the recommended approach. The bulletins that each committee produce are available for viewing using Adobe Acrobat. Subscribers to the service can access the full text of all data items. Non subscribers may view abstracts of each Data Item. An FAQ, glossary and technical notes are also available.

European Aeronautics Science Network (EASN)

This is a three year funded project which aims to bring the European universities with aeronautics activities into an integrated network, operating in parallel with industry and the national research establishments. EASN has a Steering Committee representing partners to oversee the activities of the network, as well as a number of Interest Groups (IGs) addressing various thematic issues. There are 10 interest areas covering Flight Physics, Aerostructures, Propulsion, Aircraft Avionics Systems and Equipment, Flight Mechanics, Integrated Design and Validation, Air Traffic Management, Airports, Human Factors, and Innovative Concepts and Scenarios. Within these areas several Interest Groups have been established for Advanced Combustion Chambers, Ageing Aircraft, Crashworthiness and Structural Impact, Emission Minimizing Flight Operations, Fault Tolerant Systems, Increased Exploitation of Composites, Manufacturing Processes and Technologies of Aero-Engines, Risk Analysis Based LCE in Aeronautics, Surface Engineering Treatments, Vortical Structures and IG Innovative Contacts and Scenarios. The central element is an open, Internet based network that will enable communication between groups and will provide access to a database. The Network Database contains Information on the university institutes with their aerospace competence profiles, companies and organisations in the aerospace supply chain, research establishments and information on national aeronautics research programmes. The web site describes the network members and provides details of each of the regional contact points. It identifies R&T areas and Interest Groups and the Universities who are engaged in research activities in these areas. The site also provides news and a list of related links.

Experimental Aerodynamics Research Team at the Georgia Institute of Technology

The Experimental Aerodynamics Research Team is part of the School of Aerospace Engineering at the Georgia Institute of Technology. The site provides background information about the team including a description of its facilities, website link to aerospace digital library, detailed information about research projects currently being undertaken, and links to abstracts of papers written by members of the team back to 1985. The full text of selected papers is available in PDF format. Links to other Web pages and information for undergraduate students is also present.

First Flight

Produced and maintained by the Open University, UK, this site provides a simple introduction into key events in the history of flight. It traces the development of models (including movies of how they might work) and the understanding of aerodynamics, including links to simple sites which explain the principles of flight. The stories of key flyers such as the Wright Brothers are also told.

Flight in an Adverse Environment

This is Research and Technology Organization (RTO) AGARD-LS-197, dated November 1994. The environment in which an airplane must operate is a major cause of aircraft accidents. This lecture series focuses on specific aspects of the environment, both natural and man-made, which are the major contributors to these accidents as follows: (1) wake turbulence and the generation of trailing vortex systems; (2) the results of an extensive flight test program concerning winter storms off the east coast of Canada including effect on aircraft operations; (3) electromagnetic effects including electrical discharge properties, in-flight test program, in-flight lightning models and lightning simulation techniques; (4) response of an aircraft to wind shear and methods of detection and quantifying this natural hazard; (5) heavy rain effects on aircraft systems performances in the light of full scale and model tests; (6) measurements of atmospheric turbulence, treatment of aircraft response to random turbulence and discrete gusts. For individual titles, see N95-14894 through N95-14900. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (50.10MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Foresight Defence, Aerospace and Systems Panel

The aim of the UK Government's Foresight Programme is to improve collaboration between government, industry and academia in order to increase national wealth and quality of life. Defence, Aerospace and Systems was one of 13 sectoral panels created in the first round of the programme to consider possible future trends and opportunities. Although no longer current the web site brings together a range of information resouces including details of Panel and Task Force members. A number of Panel reports and other publications produced between 1999 and 2002 are available online.

Guide to the measurement of the transient performance of aircraft turbine engines and components

This is Research and Technology Organization (RTO) AGARD-AR-320, dated March 1994. This report provides a guide for the measurement of transient aerothermodynamic performance parameters of aircraft gas turbine engines or components for engine developers, test agencies, certifying authorities, and operators of overhaul facilities and aircraft. It may be treated as an extension of AGARD Advisory Reports AR-245 and AR-248. It includes discussion of recommended procedures for the transient measurement of pressures, temperatures, flows, component geometry including rotational speed and clearances, thrust, torque, and the use of the engine control system for transient parameter measures. Typical examples are presented. A section on data acquisition and processing is included. Higher frequency dynamic measurements are excluded. Two examples, the measurement of compressor ratio and air flow at surge and a measurement of engine acceleration time are discussed in detail. This Advisory Report was prepared at the request of the Propulsion and Energetics Panel of AGARD. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (19.39MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Heat Transfer and Cooling in Gas Turbines

This is Research and Technology Organization (RTO) AGARD-CP-527, dated February 1993. The symposium was arranged in the following sessions: turbine blades--external heat transfer; turbine blades--internal heat transfer; measurement techniques; rotating disks, labyrinth seals, and shafts; combustors; design, interactions; and prediction methods. Heat transfer and cooling in gas turbines are still key factors for achieving high performance, increased life, and improved reliability. Any progress in this field will lead to a reduction of maintenance cost and fuel consumption. The purpose of the symposium was to bring together experts from industry, research establishments, and universities to discuss fundamental and applied heat transfer problems relevant to gas turbines, to exchange practical experience gained, and to review the state of the art. For individual titles, see N93-29927 through N93-29964. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (156.97MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

High-Lift System Aerodynamics

This is Research and Technology Organization (RTO) AGARD-CP-515, dated September 1993. This report includes the 32 technical papers developed for the High-Lift System Aerodynamics Symposium along with an edited transcript of the Round Table Discussion and a Symposium Evaluation Report. The symposium objectives were to address (1) how the most appropriate high-lift system can be selected; (2) how an efficient design can be produced; and (3) the experimental and analysis techniques which are necessary to explore and enhance the performance of a high-lift system. Thus, although the aerodynamics of high-lift systems was the dominant theme, the very pertinent aspects of weight, simplicity, reliability, and structural and mechanical integrity were an integral part of the Symposium, and were treated in the papers presented. In this sense, this Symposium has attempted to take a broader view of the high-lift system than has been taken by similar conferences in the past. For individual titles, see N94-18416 through N94-18447. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (120.20MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Institute for Aerospace Research

The Institute for Aerospace Research (IAR) is Canada's national aerospace laboratory. This site provides a range of introductory information which includes online access to the current strategic plan. The core content of the site is devoted to the four constituent IAR laboratories: Aerodynamics; Flight Research; Structures, Materials and Propulsion and Aerospace Manufacturing Technology. Each of these sections contain largely descriptive information on specific areas of research interest and expertise. The full-text of IAR Flyer, a newsletter, is also available online.

Integrated Airframe Design Technology

This is Research and Technology Organization (RTO) AGARD-R-794 , dated December 1993. Integrated airframe design embraces the concept of bringing together all of the aspects of airframe design, including various disciplines such as structures, materials, aerodynamics, controls, and manufacturing, from conceptual design all the way through manufacturing. It also includes the sub-disciplines which are involved in each discipline and the interactions these have with one another. Moreover, an IAD process also affects the organizational structure of the personnel. In order to provide a broad-based approach to evaluating and identifying future research and development directions required to provide IAD technology, the First Integrated Airframe Design Technology Workshop, sponsored by AGARD, was held in Antalya, Turkey on 19-20 Apr. 1993. This document summarizes the output of that Workshop. For individual titles, see N94-24314 through N94-24327. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (46.29MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Integrated Multidisciplinary Design of High Pressure Multistage Compressor Systems

This web site provides access to a Research and Technology (RTO) educational note, RTO-EN-001, dated September 1998. The publication was prepared in order to support a Lecture Series under the sponsorship of the Applied Vehicle Technology Panel and the Consultant and Exchange Programme of RTO presented on 14-15 September 1998 in Lyon, France, on 17-18 September 1998 in Cologne, Germany, and on 22-23 September 1998 in Cleveland, USA. The lecture series covers a number of topics including: flow simulations with special reference to 3D computations and to stage stacking and interactions in multistage compressors; modelling fluid structure interactions; and first order manufacturing constraints and requirements. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text of the document (34.7 Mbytes) can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Internet for Aeronautical Engineering

Produced by information specialists at Cranfield University, this is part of the Intute Virtual Training Suite (VTS), an initiative designed to teach Internet information skills to the UK Higher Education community. However, the free tutorial is potentially useful to everybody who wishes to improve their subject knowledge of aerospace and defence on the Internet. It takes the form of a "teach yourself" tutorial and includes quizzes and exercises for learners to test their knowledge. It has four main components - a 'Tour' of useful high quality Web sites, 'Discover' gives tips on how to improve searching skills, 'Judge' emphasises the need for critical evaluation of information on the Internet and 'Success' offers practical examples of people using the Internet successfully.

Introduction to the Aerodynamics of Flight

The web site provides access to NASA Special Publication, NASA SP-367, by Theodore A. Talay, published in 1975. This is very much an aerodynamics primer. Its content includes: a short history of flight, background information, fluid flow, subsonic flow effects, transonic flow, supersonic flow, beyond the supersonic, performance, stability and control, appedices and bibliography. The full text is available online in HTML format.

Investigation of Type II and Type IV Aircraft Ground Anti-Icing Fluid Aerodynamic Certification Standards

This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA AR-03/55, by Arlene Beisswenger, Guy Fortin, and Jean-Louis Laforte, dated July 2003. The certification process for aircraft ground anti-icing fluids involves flat-plate wind tunnel aerodynamic flow-off tests. This test method was developed in 1990 from flight and wind tunnel test results of full-scale and model airfoils and flat plates. The resulting lift losses were then correlated to the Boundary Layer Displacement Thickness (BLDT) on a flat plate. This correlation was made for Type II fluids existing at the time. Since the introduction of Type IV fluids in 1994, with significantly longer anti-icing endurance times, the same test procedure was applied. However, Type IV fluids are generally more viscous than Type II fluids of the same concentration. At the Federal Aviation Administration�s request, a study was undertaken to determine if aerodynamic certification testing should be different for Type IV fluids compared to Type II. The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library.

Italian Aerospace Research Centre

This is the homepage of the Italian Aerospace Research Centre (CIRA), a non-profit making research consortium which carries out the Italian National Aerospace Research Programme (PRORA). The site gives an introduction to the organisation and the scientific and the educational areas covered. It describes CIRA's aerospace activities (which include fluid dynamics, air structures, flight systems and computer science) and testing facilities (which include a plasma wind tunnel, an icing wind tunnel, a transonic research wind tunnel and an aerospace structures impact facility. The projects area of the site describes work being carried out on unmanned aerial vehicles and unmanned space vehicles. The educational area covers topics such as flight safety, pssengers comfort, air transportation and access to space. The general support area provides access to the Library Catalogue. The CIRA Newsletter is also available.

Juneau Airport Wind System (JAWS) Wind Sensor Severe Weather Performance Test Report

This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/CT-TN02/18, by William Benner, Thomas Carty, Michael McKinney and Francis Law, dated August 2002. The purpose of the field investigation was to assess the severe-weather performance capabilities of wind sensors currently used in the prototype JNU Wind Hazard Information System (JWHIS) developed by the National Center for Atmospheric Research (NCAR).The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library

Lawrence Hargrave : Australian Aviation Pioneer

The site is intended to highlight the work and legacy of a number of Australian aviation pioneers including Lawrence Hargrave, John and Reginald Duigan, and Keith Meggs. It is the work of two academics from Monash University. The site contains biograhical notes, an extensive bibliography, a gallery of images, timelines, and a listing of Hargrave's papers, some of which are available online. A number of technologies of current interest are also highlighted including tailless aircraft (flying wings) and Micro Air Vehicles. The MAV pages in particular provide a very extensive set of links to related web resources. These cover the following topics: Bird and Insect Flight Ornithopters; Micro Air Vehicles (MAVs) and related projects; Blimps and Other Flying Objects; Miniature Engines; and Minature Robotics. The site also provides an anthology of aviation pioneers.

Loades PLC

Loades PLC is predominantly involved in vehicle body design for automobiles. The site offers a guided tour of its facilities and services which include: design engineering, pattern shop, sheet metal fabrication and precision engineering. There is a gallery of photographs of both the plant and completed car body designs. CAD-CAM capabilities are described and there is a client list provided. The site is currently review (January 2006)

Low Takeoff Rotation Speed Commuter Type Aircraft Aerodynamic Performance of Type II and Type IV Fluids

This technical report (DOT/FAA/AR-03/47) was produced by the Aviation Research office of the Federal Aviation Administration (FAA) in August 2003 and was written by Arlene Beisswenger and Jean-Louis Laforte. Type II and Type IV aircraft ground anti-icing fluids are currently used on commuter type aircraft, although they are being certified to AMS1428 Annex B, which corresponds to aerodynamic acceptance test for large transport type jet aircraft whose takeoff rotation speeds generally exceed 100 to 110 knots. Some aircraft manufacturers have indicated certain performance adjustments or other commuter type operational procedures to be followed for selected aircraft when operators employ these Type II and IV fluids. At the request of the Federal Aviation Administration (FAA) William J. Hughes Technical Center, The Anti-icing Materials International Laboratory conducted AMS1428D Annex C Flat Plate Elimination Tests (FPET) for commuter type aircraft to ascertain their level of performance. The aerodynamic acceptance tests were conducted at three temperature intervals for two Type II fluids and three Type IV fluids in their neat, 75/25 and 50/50 dilution forms. A deicing and anti-icing fluid is considered acceptable at a test temperature if none of the independent boundary layer displacement thickness measurements are greater than the acceptance criteria defined by the military fluid that is tested simultaneously. The results showed that all the 50/50 dilutions are acceptable for the low-speed ramp down to minus 10 degrees Celsius, the lowest temperature tested due to freeze-point restriction. Three of the five 75/25 dilutions are acceptable for the low-speed ramp down to minus 10 degrees Celsius; below this temperature none of the fluids were acceptable. For the two other fluids, one was acceptable only at 0 degrees Celsius, the other was not acceptable at any temperature. For the fluids in their neat form, only one was acceptable at 0 degrees Celsius. For all the other fluids, the neat FPET results wer greater than the acceptance criteria. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Low-Level and Nap-of-the-Earth (NOE) night operations

This is Research and Technology Organization (RTO) 5. AG-CP-563, dated January 1995. Tactical rotary wing and low-level, fixed wing aircraft operating in high threat areas require improvements in night and adverse weather conditions in order to increase survivability, improve operational performance, and reduce pilot workload. Recent developments and the results of on-going programs suggest that increased automation and optimized integration of sensors, guidance/navigation, control and display systems, and weapons provide approaches to greatly enhanced capability in night operation. The purpose of this symposium is to support the evolutions and envelopment of alternative core structures which will lead to the fielding of effective low-level and N.O.E. night operations systems for fixed and rotary wing aircraft. For individual titles, see N95-32487 through N95-32505. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (74.9MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Manual on aeroelasticity - Subject and author index

This is Research and Technology Organization (RTO) AGARD-R-578, dated January 1971. This report is the Subject Index and Author Index cover all the chapters in the six looseleaf volumes of the Manual on Aeroelasticity and was up to date in April 1970. Since that date new chapters of the Manual have been published in the AGARD Report series. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (3.68MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Mathematical Models of Gas Turbine Engines and their Components

This is Research and Technology Organization (RTO) AGARD-LS-198, dated December 1994. This Lecture Series will present and discuss the scientific problems of modern mathematical simulation of gas turbine engines and their components. Some peculiarities of complex multicomponent and multidisciplinary models for whole flow passage of bypass gas turbine engine, core, multistage compressors and turbines, and other engine components will be studied. Solutions of steady and unsteady problems are given using high efficiency monotone numerical methods and the theoretical bases of these methods are presented. Many practical results of aerodynamic and thermostress simulations for engine components are shown. These results are compared widely with experimental data for accurate verification of developing computational codes. This Lecture Series, endorsed by the Propulsion and Energetics Panel of AGARD, has been implemented by the Technology Cooperation Program. For individual titles, see N95-19018 through N95-19026. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (38.46MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library

Missile Aerodynamics

This is Research and Technology Organization (RTO) AGARD-R-804 dated June 1994. Lecture notes for the AGARD Fluid Dynamics Panel (FDP) Special Course on 'Missile Aerodynamics' have been assembled in this report. The aim and scope of this course was to present the current state of the art on specific topics of tactical missile aerodynamics. Specifically, topics and methods covered include: Aeromechanical Design of Modern Missiles, Semi-empirical Predictive Tools, Lateral Jet Control, High Angle of Attack Aerodynamics, Analysis and Modelling of Missile Infrared Radiation, Navier-Stokes Computations for Complete Missile Configurations, and Navier-Stokes and Euler Computations for Supersonic Air Intakes. The material assembled in this report was prepared under the combined sponsorship of the AGARD Fluid Dynamics Panel, the Consultant and Exchange Program of AGARD, and the von Karman Institute (VKI) for Fluid Dynamics. For individual titles, see N95-14446 through N95-14452. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (47.50MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Multidisciplinary Design Optimization of a Strut-Braced Wing Transonic Transport

This is the full text of a paper (AIAA 2000-0420) presented at the 38th Aerospace Sciences Meeting and Exhibit, held on 10th - 13th January 2000 in Reno, Nevada. It is written by a team of authors from Virginia Polytechnic Institute and State University, and the University of Florida. The paper published by the American Institute of Aeronautics and Astronautics (AIAA) suggests an alternative wing configuration for a transonic airliner. It is in PDF format.

Multilingual Aeronautical Dictionary

This is Research and Technology Organization (RTO) AGARD-GL-1, dated January 1980. A multilingual dictionary to aid scientists, engineers, and translators in the field of aeronautics was developed. The dictionary contains an alphabetical list of English terms, accompanied by English language definitions and translations of each term int. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (1.92MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

NASA Advanced Supercomputing Division

Based at NASA Ames Research Center, the NAS Systems Division is part of the Information Sciences and Technology Directorate. The Division's mission is to develop, demonstrate, and deliver high perfomance computing capabilites to support NASA projects and missions. The NAS Division is leading the effort to build and test NASA?s Information Power Grid (lPG), a network of high performance computers, data storage devices, scientific instruments, and advanced user interfaces. The web site provides an introduction and overview of NAS activities including: mission and goals; research and technology; projects; resources; organisational structure; collaborators; history of achievement; feature stories and press releases. Gridpoints, the Division's quarterly published in-house journal, can be accessed online in PDF format. The papers and reports section provides full text access to technical reports, grant reports and conference papers produced by NAS staff. A selection of software programmes for visualizing computational fluid dynamics and other data are available for downloading. The site also offers sample datasets that represent simulations computed by researchers on systems at the NAS facility including: Multi-Component wing; Space Shuttle Launch Vehicle; Delta wing at 40 degrees angle of attack; Ring galaxies; Blunt fin; Tapered cylinder; Flat plate; Impinging jet; Liquid oxygen post; Substructures in turbulent spots; and Plot3D tutorial data (wingbodytail). The site contains a media resources section which includes press releases, feature stories, fact sheets, and a multimedia Library of high-resolution photos, graphics, and video clips.

National Aerospace Laboratory (NLR)

This is the home page of the NLR, an independent non-profit research institute based in the Netherlands. It undertakes research for both national and international customers. The site provides background information about the institute including its annual report and latest news. A section of the site is devoted to describing NLR's research activities, which are within civil and military aviation, aircraft development, space technology and non-aerospace applications of aerospace technology.

National Aerospace Technology Strategy Implementation Report

The United Kingdom's The Aerospace Innovation and Growth Team (AeGIT) report on the Future of the UK Aerospace Industry, (Executive Summary (Vol A), Overview Report (Vol B)) published in July 2003, recommended the establishment of a National Aerospace Technology Strategy (NATS) as a partnership between Government, Industry and Academia. This follow-up report, published in August 2004, defines the background, process and structures necessary for the implementation of the AeGiT's strategy. The Implementation Report recommends the establishment of Aerospace Innovation Networks to carry out focused research followed by validation carried out through Aerospace Technology Validation Programmes, all of which involve industry, university and research establishment partners supported through balanced and coordinated industry and government funding. Furthermore, the report outlines the organisational structure required to carry forward the Technology work programme, this being done through an Aerospace Technology Steering Group interacting with the R&T Sub Group of the National Defence Industry Council. The full text of the report is available for downloading from the AeIGT website

NATO Research and Research Technology Organization (RTO)

The Research and Technology Organization is the focus for defence research and technology activities within NATO. It was formed by a merger of the Advisory Group for Aerospace Research & Development (AGARD) and the Defence Research Group (DRG). The RTO web site provides access to a wide range of information resources. The mission, objectives history, and organisational structure of the RTO are described. An events calendar provides details of RTO activities. The site provides details of the work programmes and publications of the RTO technical panels, the Information Management Committee (IMC) and the Modeling and Simulation Group. A growing number of RTO reports are also available online, and the site provides access to searchable abstracts and Full Text Publication Library. There is also a link to the Science, Technology and Research Network (STARNET), which has been developed by the IMC as a means to facilitate access to existing information resources worldwide.

NATO Research and Technology Organization (RTO) : Full Text Publication Library

The web site provides access to a collection of full text documents produced by the NATO Research and Technology Organization and its predecessor, Advisory Group for Aerospace Research & Development (AGARD). The collection includes the following report series: RTO-AG (Advanced Guidance for Alliance Research and Development); RTO-MP (Meeting Proceedings);RTO-EN (Education Notes); RTO-TR (Technical Reports); RTO-TM (Technical Memoranda); RTO-Misc (Miscellaneous Publications); AGARD-AG (AGARDographs); AGARD-R (Reports); AGARD-AR (Advisory Reports); AGARD-CP (Conference Proceedings); AGARD-LS (Lecture Series); and AGARD-Misc (Miscellaneous Publications). The browse facilityprovides access to abstracts, Tables-Of-Contents and Full Text. Currently the search option is under construction.

Naval Postgraduate School : Department of Aeronautics and Astronautics

The Web site provides details about the Department, courses, research projects and laboratories. It is also possible to download a copy of the department brochure in PDF format. Of particular note is the 'Online Tools' section which contains Panel Code V1.2 for NACA 4 and 5 digit airfoils, Panel Code V2.0 for NACA 4/5-digit & UIUC database airfoils, and a Transonic Small Disturbance Solver, all of which can be freely viewed and downloaded.

Nielsen Engineering & Research (NEAR)

NEAR provides consulting services and specialized software for aerodynamic analysis and design, especially launch vehicle aerodynamics, missile aerodynamics, and store separation. The web site provides a brief company overview. The company's research and development areas are described. These include: CFD, computational modeling, and fluid mechanics; aerodynamic prediction and design; flow control devices, microelectromechanical systems (MEMS), sensors; information technologies and intelligent systems; and mathematical modeling. These descriptions contain links to some full text papers produced by NEAR personnel. Other sections of the site cover consulting services and expertise, software products, hardware products, and publications for sale.

Nonplanar Wing Concepts For Increased Aircraft Efficiency

This report is part of VKI lecture series on Innovative Configurations and Advanced Concepts for Future Civil Aircraft, created in June 6-10, 2005 by I. Kroo Stanford University, U.S.A. This report deals with nonplanar wings which offer the possibility of reduced drag compared with planar wings of the same span and lift. However, aircraft are not compared on the basis of drag with fixed span and lift, making the integration and assessment of nonplanar wing concepts complex. This paper deals with some of these issues. A brief review of several concepts from winglets to ring wings is followed by a more detailed look at recent ideas and their application to future transport aircraft. Results suggest that potential efficiency gains may be significant, although non-aerodynamic and off-design characteristics are critical in determining the utility of these concepts for transport aircraft.

Numerical Methods for 1D Compressible Flows : An Interactive Book

This is an interactive text book produced by M. Manzinni, A. Ticca and G. Zanetti of the Center for Advanced Studies, Research and Development, Sardinia, Italy. The book aims to present numerical methods for the solution of 1D compressible problems. The book is divided into three separate parts - a description of the issues involved, a discussion of the numerical methods involved and interactive examples. It is in HTML format.

Office National d'Etudes et de Recherches Aerospatiales (ONERA)

Office National d'Etudes et de Recherches A�rospatiales (ONERA) is the French national aerospace research establishment. It is a scientific and technical public establishment managed according to industrial and commercial practice, placed under the supervision of the Minister of Defense. Its missions are to develop and guide aerospace research; design, develop and implement the facilities it requires to conduct its research and testing; publish and promote the results of its research; and contribute to the education of engineers and scientists. In addition to an overview of current research projects and interests, facilities and expertise, the site does provide a searchable database of scientific publications. This includes articles published in journals, papers delivered before conferences, theses, Technical Notes (NT), other publications, but not unpublished research reports. Some recent documents are available in full text format. An French language version of the site is also available.

ONERA Publications Database

ONERA (Office National d'Etudes et de Recherches Aerospatiale) is the French national aerospace establishment which has expertise in all the disciplines involved in aircraft, spacecraft and missile design. The ONERA database allows for searching of journal articles, papers delivered at conferences, theses, Technical Notes (NT), and other publications. Unpublished ONERA research reports are not included. The full text of selected recent documents is available in PDF format. It is possible to search by author name, information contained within the bibliographic record or the full text (if it is available). Searching in the full text field will return full text reports only.

Open Channel Foundation : Aerodynamics Applications

The aim of this US based organisation is to publish innovative open source software for a wide range of scientific and engineering applications. A number of these relate to aerodynamics applications. These include subsonic aerodynamic analysis of wing flaps in combination with canard or horizontal tail surfaces; oscillatory airloads on blades; aircraft brake performance during rollout; wake rotor inflow / wake velocity prediction; the generation of two-dimensional finite-difference grids; mission analysis; minimisation of fuel burn or direct operating costs; a flow solver for airfoils and turbomachinery blade rows; computation of potential flow fields; performance prediction of an airframe integrated scramjet; and determination of the mean camber surface of trimmed noncoplaner planforms with minimum vortex drag.

Open Channel Foundation

The aim of this US based organisation is to publish innovative open source software for a wide range of scientific and engineering applications. Much of the software available from the site has been produced from within the academic and research community. Over 200 software programmes are available. The site offers search and browse access to the software. The list of disciplines covered includes aerodynamics, antenna design and satellite communications; CAD CAM CAE, crack growth and fatigue analysis; digital signal processing, failure analysis, finite element analysis, life support systems, navigation and radar, optics and lasers, spacecraft design, and trajectories and orbital mechanics.

Optimization Techniques Exploiting Problem Structure : Applications to Aerodynamic Design

This web site provides access to a Virginia Polytechnic Institute and State University Department of Aerospace and Ocean Engineering PhD dissertation, by Ajit R. Shenoy, dated 11 April 1997. The dissertation investigates the use of all-at-once methods applied to aerodynamic design, with particular reference to Reduced Hessian and Sparse Optimization techniques. A number of design problems are studied including: a nozzle in a one-dimensional transonic flow; temperature control, and transonic airfoil design. Bibliographic and abstract details are available in HTML format. The full text of the document is accessible online in PDF format [2.80 Mb]. This title is part of Virginia Tech�s Electronic Thesis and Dissertation Collection (VT ETD).

Persistent and Critical Issues in the Nation�s Aviation and Aeronautics Enterprise

This report was released by the Aerospace Division of the American Society of Mechanical Engineers (ASME), Washington, DC, November 2003. A Steering Committee consisting of members of key United States engineering and aerospace associations was asked by the Office of Science and Technology Policy (OSTP) to provide the engineering community's perspective on prioritizing technologies critical to the long-term health of the nations's civil and military aviation and aeronautics technology enterprise. This statement summarises the Steering Committee�s findings and recommendations. It includes an overview of cross-cutting technology and policy issues, as well as individual sections covering aerodynamics, aircraft propulsion, avionics and embedded information technology, flight mechanics and control, information technology in design, and structures and materials. The text is available in PDF format. Useful tables and figures include Uninhabited Air Vehicles (UAV) Project Count, by Country of Development; National Aeronautics and Space Administration Aeronautics R&T Funding; U.S. Department of Defense Aeronautics R&T Funding; Aerospace Engineering Degrees Awarded; Graduate Degrees In Aeronautical Engineering, U.S. and Foreign; and a List of Recent X-plane Prototype Programmes.

Prediction of Antisymmetric Buffet Loads on Horizontal Stabilizers in Massively Separated Flows, Phase II : Final Report

This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-99/27, by Saeed Farokhi and others, dated May 1999. The report describes a low cost technique for the prediction of full-scale buffet loads on horizontal stabilizers. The full text of the report is available in PDF format from the online catalogue of the FAA William J. Hughes Technical Center Library.

Preliminary Design of a Blended Wing Body Configuration using the Design Tool PrADO

This conference paper was written by C. Osterheld, W. Heinze and P. Horst from the Institute of Aircraft Design and Lightweight Structures (IFL) at the Technical University Carolo-Wilhelmina at Brunswick. It was given at the CEAS Conference on Multidisciplinary Aircraft Design and Optimisation, held at K�ln on 25th-26th June 2001. New, unconventional aircraft configuations liked the blended wing body (BWB) are expected to significantly improve the economic efficiency of future air transport. In order to investigate potential improvements and to predict major design challenges of this new class of aircraft, the modelling and analysis capabilities of the in-house aircraft design tool of IFL, PrADO, have been adapted to the BWB requirements. Therefore a parametric geometry model was defined and implemented for geometric sizing and to supply input for physics-based analyses methods (FEM, aerodynamic panel method, drag and weight prediction). In this paper the methods used and the modelling and analysis capabilities of the improved, BWB-specific PrADO system are described. This paper is provided in PDF format.

Proceedings of the Institution of Mechanical Engineers, Part G : Journal of Aerospace Engineering

Published six times a year, the Journal of Aerospace Engineering is a forum for the communication of ideas and methods presently in use at the forefront of technology in the field of aerospace engineering. It contains papers on both theoretical and practical aspects of all types of civil and military aircraft and spacecraft and their support systems. The scope is wide, covering research, design, development, production, operation, servicing and repair, components and auxiliary equipment, safety and reliability. The site provides contents information for the journal. If you wish to view full text check with your library to see if they have a subscription.

Progress Through Partnership : 12 - Defence and Aerospace

This web site provides access to one of a series of reports published as part of the first UK Technology Foresight programme, in March 1995. The Defence and Aerospace Panel report describes the strategic issues and priorities which emerged from an extensive programme of analysis and consultation. The report presents a series of furture market scenarios, along with a set of key technical priorities and recommendations. The sectors covered in the report include: defence, civil aerospace, and space. The full text is available in HTML format.

Propulsion and energetics panel working group 14 on suitable averaging techniques in nonuniform internal flows

This is Research and Technology Organization (RTO) AGARD-AR-182, dated June 1982. Numerous investigations were made into how the average properties across a nonuniform or unsteady flow to characterize it for the purpose of one dimensional performance of a gas turbine powerplant. Collection and review of existing practice or proposal for averaging nonuniform and or unsteady flows; identification of averaging techniques to calculate heat, power, thrust, and efficiency; qualification where applicable of uncertainty levels of different averaging methods, recommendation of methods for adoption, and recommendation of further research activities to resolve uncertainties were studied. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (4.47MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Quality assessment for wind tunnel testing

This is Research and Technology Organization (RTO) AGARD-AR-304, dated July 1994. The wind tunnel continues to be the main instrument for providing experimental aerodynamic data to the aerospace industry and the aerodynamic researcher for the purpose of load and performance evaluation of theoretical results. In both cases, it is imperative that the user has confidence in the quality of the results, which means that he must have information of what accuracy to attach to the data. This report describes a practical approach for assessing the uncertainty of experimental measurements. Although it concentrates on aerodynamic references data, the approach presented can be used to report data and associated uncertainties for any other condition. The methodology described is designed to facilitate communications and to encourage professional and practical analyses of complex problems. The most recent accepted technical concepts have been included in the methodology. This report presents the results of a study by Working Group 15 of the AGARD Fluid Dynamics Panel. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (6.97MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

R&D Intensive Businesses in the UK

This is UK Department of Trade and Industry (DTI) Economics Paper No. 11, published in March 2005. The UK Government?s ten-year framework for investment in science and innovation, published in 2004, set a challenging target for a step-change in levels of Research and Development (R&D) in the British economy. This paper is part of the DTI's evolving assessment of the UK's science, technology and innovation performance. It forms part of a broader annual assessment by the Government of the UK?s performance across the full range of outputs and attributes of the UK?s science and innovation system. The paper shows that along with pharmaceuticals, the aerospace industry is one of most R&D intensive sectors within UK manufacturing. The text of the paper is available in PDF format (288 KB).

Report of the high Reynolds number wind tunnel study group of the Fluid Dynamics Panel

This is Research and Technology Organization (RTO) AGARD-AR-35, dated April 1971. Modern aeronautical and aerospace systems are so expensive that every reasonable effort to minimize the risk in their development is warranted. If a weapon system like the F-I11 or an airplane like the Concorde suffers delays or outright failure as a result of unforeseen technological problems, the penalties to the companies and nations involved are staggering. The tried and proven way to minimize such risks on aerodynamic systems is to conduct extensive tests in adequate wind tunnel facilities. Higher costs of the future, large sophisticated aeronautical and aerospace systems make such testing even more imperative than is indicated by history. Wind tunnels of the NATO countries have been shown, during recent years, to be quite inadequate for tests for the large aeronautical systems under development. The intricacies and inaccuracies associated with extrapolation of wind tunnel data taken at a Reynolds number of 3 to 7 million for design of airfoils that operate at Reynolds numbers of over 150 million were thoroughly discussed at the von Krirmrin Institute’s lecture series on “Large Airplane Aerodynamics” . The study reported herein is adequate for the purposes of defining the performance and operating characteristics required in new, high Reynolds number wind tunnels, and conceptual tunnel designs which meet these requirements are proposed. Although the attention of the HIRT group was devoted almost exclusively to the transonic flight regime, the proposed tunnels could be designed to meet the high Reynolds number testing requirements throughout the transonic speed range. The wind tunnels recommended in this report can be built using existing technology. However, utility of the tunnels and the quality of the data that they will yield will be enhanced by vigorous support of a relevant research program. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (8.01MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Scale Effects on Aircraft and Weapon Aerodynamics

This is Research and Technology Organization (RTO) AGARD-AG-323, dated July 1994. The present state of knowledge on scale effects at high lift and low speeds, at transonic speeds, and on aircraft drag are presented. In addition, scale effects in various important specific scale-sensitive areas such as forebody vortex flows, the flow in and near open cavities, the flow into an air intake, the flow over propellers, and on ice accretion simulation testing are discussed. The emphasis is on scale effects that have been observed in flight-tunnel comparisons for specific aircraft. It is concluded that much has been learned about scale effects; however, precise prediction can still be difficult. Twenty recommendations for further research are mentioned. This AGARDograph has been produced at the request of the Fluid Dynamics Panel of AGARD. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (24.07MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

School of Aeronautical Engineering at Queen's University, Belfast

The School of Aeronautical Engineering has research interests in the following areas: aerodynamics, aircraft structures and integrated aircraft technology. The Web site provides information about past and current projects that are being undertaken in these fields and selected papers produced by staff. It also contains details of the courses on offer by the department as well as a full staff list with biographies.

Science Tracer Bullets Online

Produced by the Library of Congress the Science Tracer Bullet series contains research guides that help you locate information on science and technology subjects. The include brief introductions to the topics, lists of resources and strategies for finding more. There is an A-Z listing available. Those of particular interest include aerodynamics (mechanics of flight), aircraft, astronomy and astrophysics, balloons and airships, chemical and biological warfare, remote sensing, and space science projects.

Sear Craft Wing In Ground Effect (WIG) Technology and Design

This site provides information about WIG vehicles including explaining how they work, history and technology development and design requirements. The site describes work carried out by Seair in the areas of experimental aerodynamics and hydrodynamics, computational prediction and simulations, and also conceptual design studies for commercial and recreational WIG craft.

See How It Flies: A New Spin on the Perceptions, Procedures, and Principles of Flight

This resource is a full text electronic textbook, written by John S. Denker, a pilot. The book is intended to appeal to pilots and anyone else who is interested in how aeroplanes behave. The idea is to concentrate on ideas that are useful in the cockpit, and to explain them as clearly as possible. The main topics are perceptions, procedures and principles. The book is available in HTML format and is broken down into chapters and subsequently into headings to aid browsing.

Simulation in Support of Flight Testing

This report is dated September 2000 and was sponsored by the SCI-005 Task Group of the Flight Test Technology Team which is part of the Systems Concepts and Integration Panel (SCI) of the Research and Technology Organisation (RTO). It was authored by Dennis O. Hines and has the report number RTO-AG-300, AC/323(SCI)TP/27, Volume 19. The report discusses how simulation can be used in flight testing of fixed-wing aircraft. The full text of this report can be viewed either by FTP, or in PDF format.

Small gas turbines for helicopters and surface transport

This is Research and Technology Organization (RTO) AGARD-LS-46, dated May 1971. This Lecture Series is sponsored by the Propulsion and Energetics Panel and the Consultant and Exchange Program. In view of the increasing interest in Small Gas Turbines for the propulsion of surface vehicles, it was felt appropriate by AGARD Propulsion and Energetics Panel to set up a team of selected experts from various NATO nations to present a series of lectures on this subject. After a survey of the field of application for Small Gas Turbines, to replace reciprocating engines for helicopters and surface vehicles propulsion, the present state-of-the-art will be reviewed together with problems related to reliability, life time, pollution regulation, weight and volume according to various applications. Conventional and advanced cycles (cycle of Nernst cycle with heat exchange) will be compared. A description of components (compressors, combustion chamber, turbines, nozzles, shafts with various configurations) will be followed by a review of industrial and technological problems. The use of Small Gas Turbines for power generation, auxiliary stand by or emergency power plant is then presented. The last paper will be a Survey of Future Possible Developments and performance improvements (mixed diesel and turbines - use of high temperature materials). A round table discussion with the participation of all the speakers will conclude the Lecture Series which will be presented in four different NATO nations (France, UK, Canada and USA) from 21 June to 2 July 1971. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (36.91MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Society of Flight Test Engineers

The Society of Flight Test Engineers (SFTE) is a fraternity of engineers, whose principal professional interest is the flight testing of aircraft and missiles. The objective of the Society is the advancement of flight test engineering throughout the aircraft industry by providing technical and fraternal communication among individuals, both domestic and international, in the allied engineering fields of test operations, analysis, instrumentation and data systems. The SFTE web site provides a range of information resources incliding: a calender of events, links to SFTE Chapters, job announcements, workshops and details of the SFTE Technical Council. The current issue of the Society's newsletter, SFTE Flight Test News, is available for downloading. A database containing citations and abstracts of SFTE symposium papers can be browsed or searched, and papers can be ordered online.

Special Course on Aerothermodynamics of Hypersonic Vehicles

This is Research and Technology Organization (RTO) AGARD-R-761 , dated June 1989. This AGARD Fluid Dynamics Panel/von Karman Institute Special Course was inspired by new ventures in the hypersonic domain moving forward on both sides of the Atlantic-HERMES in Europe and the NASP (X-30) in the United States. Following the review of basic principles including real gas effects, a series of lectures were presented on experimental and computational methods specific to hypersonic flows. Stress was placed on measurement techniques developed primarily for flows with heat transfer, chemical reactions, strong shocks, and compressible boundary layers. Both surface measurements and flow field measurements including species concentration techniques, were discussed. The same spirit governed the lecture on computational methods: stress was placed on the new problems in CFD posed by high speeds and chemical reactions. The course finished with state of the art reviews on three critical flow problems: transition to turbulence; ininteractions between shocks and boundary layers; and shock/shock impingement. For individual titles, see N89-29307 through N89-29315. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (65.42MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Special Course on Progress in Transition Modelling

This is Research and Technology Organization (RTO) AGARD-R-793 , dated April 1994. Lecture notes for the AGARD Fluid Dynamics Panel (FDP) Special Course on 'Progress in Transition Modelling' have been assembled in this Report. The aim and scope of this Course was to provide information on new developments in modelling the dynamics of transition to turbulence, and the prediction of transition in boundary-layer flows. Specifically, topics and methods covered include: a physical description of boundary-layer transition, linear theory, asymptotic techniques, parabolized stability equations, direct numerical simulations, empirical methods and closure of the Reynolds' averaged Navier-Stokes equations. The material assembled in this report was prepared and presented under the combined sponsorship of the AGARD Fluid Dynamics Panel, and the von Karman Institute (VKI) for Fluid Dynamics. For individual titles, see N94-33885 through N94-33890. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (43.13MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Special course on Shock Wave/Boundary Layer Interactions in Supersonic and Hypersonic Flows

This is Research and Technology Organization (RTO) AGARD-R-792 , dated August 1993. Notes for the AGARD Fluid Dynamics Panel (FDP) Special Course on 'Shock-Wave/Boundary-Layer Interactions in Supersonic and Hypersonic Flows' are presented. The objective was to report on results from recent research programs providing a consolidated review of these activities and a sound basis for developing more reliable methodologies for future vehicle design. The course also provided a focused review of recent progress for swept interactions in both laminar and turbulent flows, including discussions: flowfield structure; scaling and similarity laws; effect of shock strength on flow feature; effect of shock generator geometry for a given shock strength; techniques for investigating swept interactions, particularly optical techniques; and contributions of numerical simulations to the understanding of swept interactions. The effects of turbulence and turbulence modeling on the flowfields are provided. For individual titles, see N94-15197 through N94-15203. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (48.50MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Stability in Aerospace Systems

This is Research and Technology Organization (RTO) AGARD-R-789, dated February 1993. This volume contains the 18 unclassified papers presented at the Guidance and Control Panel Workshop. The presented papers cover topics under the following headings: fundamental aspects of stability with examples; basic theoretical aspects and chaos; and applications of aerospace techniques. For individual titles, see N94-11490 through N94-11504. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (53.52MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Statistical Modeling of Simulation Errors and Their Reduction Via Response Surface Techniques

This web site provides access to a Virginia Polytechnic Institute and State University Department of Aerospace and Ocean Engineering PhD dissertation, by Hongman Kim, dated 18 June 2001. The thesis invesigates errors of computational simulations in the design of high-speed civil transport (HSCT) aircraft. Bibliographic and abstract details are available in HTML format. The full text of the document is accessible online in PDF format [725.88 Kb]. This title is part of Virginia Tech�s Electronic Thesis and Dissertation Collection (VT ETD).

Steady and Transient Performance Prediction of Gas Turbine Engines

This is Research and Technology Organization (RTO) AGARD-LS-183, dated May 1992. Aero-thermodynamic performance prediction methods for gas turbine engines with respect to steady and transient operation are discussed. This includes advanced cycle calculation methods, also taking into account variable cycle engine types. A very important objective is the consideration of installation effects, i.e., Reynolds number and inlet distortions, as well as advanced control concepts for increasing engine surge margins. In addition to these topics, individual papers include practical considerations in designing the engine cycle, dynamic simulation, inlet distortion effects in aircraft propulsion system integration, 'smart' engines, and performance and health monitoring models. For individual titles, see N92-28459 through N92-28467. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (8.30MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Supercavitating Flows

This web site provides access to a NATO Research and Technology Organization (RTO) document, RTO-EN-010, January 2002. It contains papers from a lecture series jointly organised by the Applied Vehicle Technology Panel (AVT) and the von K�rm�n Institute in Brussels, Belgium, presented 12-16 February 2001. The lectures cover a range of topics including theoretical aspects, modelling, mathematical, numerical and experimental studies and results, applied to 2D foils or struts, 3D hydrofoil wings, propellers, cascades, surface piercing propellers, and axisymmetric (or quasi-axisymmetric) bodies including water entry phenomena. The citation and abstract information are in HTML format, and the full text is available online in PDF format (40.2 Mbytes).

Supersonic Aircraft Optimization for Minimizing Drag and Sonic Boom

This is a dissertation for the degree of doctor of philoshophy written by Martin K. Chan submitted to the department of Aeronautics and Astrophysics of Stanford University in 2003. This thesis describe a design tool incorporating classical sonic boom theory, computational fluid dynamics and a multi-objective genetic algorithm. This tool was developed for low-boom supersonic aircraft optimization. Both sonic boom and drag were optimized simultaneously and a Pareto optimal set of designs ranging from minimum boom to minimum drag was obtained for each optimization. Since sonic boom was optimized directly, the method had broader applicability than the traditional inverse method. A high-order three-dimensional panel method was used for sonic boom prediction. The traditional linear source model was fast but did not account for wing-body aerodynamic interaction. Euler solutions were expensive for computing sonic booms because a large number of grid points were needed to accurately predict the pressure signature away from the aircraft. For the Mach number and configurations of interest, the panel code showed good agreement with Euler but at a fraction of the cost. A loudness metric was shown to have advantages over initial overpressure and peak overpressure for measuring shaped sonic booms. However, optimization results obtained using calculated loudness raised concerns about the robustness of the solution to atmospheric disturbance. Peak overpressure minimization also produced reasonable sonic boom signatures and appeared more robust to atmospheric uncertainties, but the resulting loudness was not as good. Better convergence was also observed with peak overpressure. Two supersonic business jets were optimized. One was a conventional configuration; the other was a natural laminar flow configuration. Optimization results obtained using loudness and peak overpressure were compared. A non-axisymmetric fuselage was optimized and found to reduce the inviscid drag by 9 to 30 percent at the same sonic boom loudness. This PhD thesis is available free in PDF format (17Mb).

Swedish Defence Research Agency

The Agency (Totalf?arets forskningsinstitut - FOI) was formed on 1 January 2001 through an amalgamation of the Swedish Defence Research Establishment (FOA) and the Aeronautical Research Institute (FFA). The site provides an overview of the organisational structure, including the Division of Aeronautics, FFA, which is made up of the core of the former Aeronautical Research Institute. There is a searchable and browsable database of FOI reports. For browsing purposes the reports are sorted by department. The text of the reports are avialable in PDF format.

Symposium on Unsteady Aerodynamics for Aeroelastic Analyses of Interfering Surfaces, part 1

This is Research and Technology Organization (RTO) AGARD-CP-80-PT-1, dated April 1971. A Symposium on Unsteady Aerodynamics for Aeroelastic Analyses of Interfering Surfaces was organized by the Structures and Materials Panel of AGARD. The papers given on this occasion have been collected in the two volumes. One of the major concerns of the Structures and Materials Panel is the development of analytical and practical methods for predicting, preventing and controlling aeroelastic problems affecting both aircraft and aerospace-craft. Whether flutter, gust response, or alleviation and mode stabilization system designs are concerned, the development of safe and efficient methods depends on the ability to predict unsteady aerodynamic forces accurately. As early as 1964, a Working Group created within The Structures and Materials Panel for the purpose of studying these forces, defined a small number of wing planforms to be used as standard models for comparing aerodynamic force prediction methods on the basis of data on vibration modes, excitation frequencies and Mach numbers. In view of the tremendous utility of such a scheme, the Panel decided in 1968 to extend this programme to include the interaction of more complex aerofoils such as T-tails or wing horizontal tail combinations. Several planforms, as well as some parameters, have been recently selected to be used as standards for comparisons. Consequently, the objectives and themes of the Symposium have been set as follows: (a) Present and discuss the latest contributions to methods for predicting unsteady aerodynamic forces in the interactions of lifting surfaces. (b) Determine the merits and limitations of various methods (c) Present applications and numerical values which can be employed to evaluate the new methods proposed. (d) Formulate suggestions about future developments and requirements. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (23.23MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

System Identification for Integrated Aircraft Development and Flight Testing

This web site provides access to a Research and Technology Organization Meeting Proceedings, RTO-MP-011, Paris, March 1999. The document contains papers presented at the the Systems Concepts and Integration Panel (SCI) Symposium held in Madrid, Spain, 5-7 May 1998. The objectives of the symposium were to review the state-of-the-art of flight vehicle system identification, and to provide a critical appraisal of current methods developed and applied to flight test data in a number of NATO countries. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (35.6 Mbytes) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library

Technical evaluation report on AGARD Specialists' Meeting on Aerodynamic Interference

This is Research and Technology Organization (RTO) AGARD-AR-34, dated May 1971. The AGARD Fluid Dynamics Panel organised a three-day Specialists' Meeting on "Aerodynamic Interference" that was held at the U.S. Naval Ordnance Laboratory. This meeting was intended to provide a forum for the discussion of theories and experiments to explain the existing comprehension of aerodynamic interference; and to provide some guidelines and design rules to improve the flight characteristics of military and commercial aircraft and weapons. The speed regimes were restricted to subsonic, transonic and supersonic mach numbers. The objectives of this report is to assess current state-of-the art of the analytical and test techniques concerned with junction flows (in terms of that which was preached and that which should have been recited, perhaps), to outline their advantages and disadvantages and to Indicate any relevant omissions. In particular, it should strive to show the practical applications of the work presented with the view of immediate help to the aircraft designer. It was considered that the report should be candid and forthright to stimulate discussion, accepting, of course, that an element of the author's personal bias would be involved. The report is split essentially into three parts: following a synopsis, an attempt is made to give a constructive review of the papers presented, subsequent to which some clear-cut conclusions are drawn. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (6.13MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Technologies for Highly Manoeuvrable Aircraft

This is Research and Technology Organization (RTO) AGARD-CP-548, dated March 1994. The new generation of combat aircraft incorporate significant advances in maneuver capability, especially in such areas as post-stall control and sustained supersonic maneuver. These technologies expand the operational capabilities, and are essential for survival in a sophisticated threat scenario, and also to obtain favorable exchange ratios against an opponent using the current generation of fighters. The aim of this symposium was to review the various technologies, which combine to give this increased operational capability, and the techniques which are available or being developed, to overcome the design problems associated with the attainment of these goals. The symposium was divided into six sessions covering propulsion and integrated flight control, aerodynamics and control at high angles of attack, post-stall flight and control, flying qualities applied criteria, agility and simulation. For individual titles, see N94-34606 through N94-34631. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (88.29 MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

The aerodynamics of parachutes

This is Research and Technology Organization (RTO) AGARD-AG-295, dated July 1987. This AGARD report discusses the principal aerodynamic characteristics of parachutes and the factors which affect them. It is anticipated that its main readers will be recent engineering graduates entering research establishments, parachute companies or related industries so some appreciation of basic mechanics, the principles of computing and elementary fluid dynamics on the part of the reader has been assumed. Its contents include Steady-State and Unsteady Aerodynamics, Parachute Deployment and Inflation, Experimental Investigations, Methods of analysis, Extraterrestrial Parachute Applications, and some suggestions for future research. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (14.42MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

The testing of fixed wing tanker and receiver aircraft to establish their air-to-air refuelling capabilities

This is Research and Technology Organization (RTO) AGARD-AG-300-VOL-11, dated December 1992. Since its founding in 1952, the Advisory Group for Aerospace Research and Development has published, through the Flight Mechanics Panel, a number of standard texts in the field of flight testing. The original Flight Test Manual was published in the years of 1954 to 1956. The Manual was divided into four volumes: (1) performance; (2) stability and control; (3) instrumentation catalog; and (4) instrumentation systems. This AGARDograph therefore describes the points that need to be considered when planning AAR trials to clear a new tanker or a new receiver aircraft for Service use. The paper assumes some familiarity with current AAR practices and equipment. It covers the two AAR systems in widespread use, namely the probe and drogue, and boom refuelling systems. Many of the points that need to be considered are common to both. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (4.50MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

The WIG Page

The site provides an introduction to Wing In-Ground effect (WIG) technology, including: history and development, aerodynamics, design concepts, take-off assistance, and applications. A list is provided of WIG craft and projects, and the descriptions include images and brief technical data. There is also a list of companies and other organisations involved in WIG activities. A searchable database of WIG craft and projects is also available. The site contains a listing of related books, conferences, television programmes and features an extensive searchable database of article and paper references. There is an annual membership charge to access the members area which contains additional features and information. The site is edited by Edwin van Opstal, and is sponsored by SE-Technology.

Theoretical and Experimental Methods in Hypersonic Flows

This is Research and Technology Organization (RTO) AGARD-CP-514, dated April 1993. Papers prepared for the AGARD Fluid Dynamics Panel Symposium on theoretical and experimental methods in hypersonic flows held on 4-8 May 1992 are presented. The objectives of the Symposium were to (1) report and assess the advances being made by the AGARD community on the development and application of theoretical methods and experimental techniques for simulating hypersonic flows over aerospace vehicles; (2) highlight outstanding problem areas; and (3) establish pointers to aid in the planning and implementation of future research programs. Major topics covered by the Symposium were testing techniques and instrumentation, computational methods and physical modeling, and validation and accuracy assessment. For individual titles, see N94-10422 through N94-10465. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (117.34MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Toward Mach 2 : The Douglas D-558 program

This web site provides access to a NASA Dryden Flight Research Centre history series publication, edited by J. D. Hunley. The publication is based on the proceedings of a symposium on the D-558 programme, held at Dryden, February 4, 1998. The publication includes an appendix containing brief technical specifications of the D-558 aircraft, as well as links to a number of other related documents. The full text is available online in HTML format.

Turbomachinery Design Using CFD

This is Research and Technology Organization (RTO) AGARD-LS-195, dated May 1994. Computational Fluid Dynamics (CFD) has become a major design tool for designers of turbomachinery. The progress in this area is fast, and the use of 3-D methods is becoming increasingly applicable to the design process. This Lecture Series will include: (1) Computational methods for preliminary design and geometry definitions; (2) Methods for computing through-flows, blade-to-blade flows and geometry generation; (3) Optimization strategies; (4) Designing in three dimensions; (5) Code validation, mesh influence on solution accuracy; (6) Turbulence and transition modelling; (7) Comparison of time averaged flow solvers and 3-D unsteady CFD codes; (8) Industrial use of CFD and the points of view of the designers. For individual titles, see N95-14128 through N95-14136. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (66.39MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

UIUC Applied Aerodynamics Group

This is the web site of the Department of Aeronautical and Astronautical Engineering University of Illinois at Urbana-Champaign. It contains a range of information resources including information on low-speed airfoil tests for model aircraft, unmanned aerial vehicles, and small wind turbines. There is a listing of current research activities and personnel in the Group. A link is provided to the UIUC Airfoil Data Site, which contains airfoil coordinates (for over 1550 airfoils) and performance data. The performance data is mostly for low Reynolds number applications. A link is also provided to The Incomplete Guide to Airfoil Usage (563 kB), which is compiled and maintained by Dave Lednicer. The guide includes a listing of what airfoils have been used on over 4000 aircraftA link to the Aircraft Dynamics Model page provides access to 20 aircraft models for use with the open source FlightGear flight simulator.

Unconventional Configurations for Efficient Supersonic Flight

This report is part of VKI lecture series on Innovative Configurations and Advanced Concepts for Future Civil Aircraft, created in June 6-10, 2005 by I. Kroo Stanford University, U.S.A. The report deals with Alternative configurations for more efficient supersonic aircraft which are suggested by consideration of the sources of drag at high speeds. Results of studies described in this paper indicate that supersonic aircraft with much higher efficiencies than previously achieved are possible with reduced Mach number. The paper focuses on two promising candidate solutions: oblique wings and configurations with supersonic laminar flow. In this paper they review some of the fundamental issues for potential efficient supersonic aircraft and describe recent work by researchers at NASA, Stanford University, and industry on unconventional configurations that may provide significant improvements in high speed efficiency.

Undergraduate Computer Programs

This is the download page for a number of Java programs and applets which were designed by staff at the NASA Glenn Research Center to help undergraduate engineering students to learn about the basics of aerodynamics and propulsion. Mach and Speed of Sound Calculator allows you to specify the altitude and speed (or Mach) of an aircraft and the program uses the standard day atmosphere mathematical model to determine the speed of sound and the Mach number (speed) of your aircraft. EngineSimU is a simulator that performs a Brayton Cycle analysis of a turbine engine or ramjet. It works in design mode and test mode so that a wide range of design variables and flight conditions can be simulated. There is an even more powerful version of EngineSimU which is available for very experienced users. This program is a Java application, not an applet. It runs stand alone and you must have Java installed on your computer to run this program. FoilSim II is a simulator that performs a Kutta-Joukowski analysis to compute the lift of an airfoil. The user can control the shape, size, and inclination of the airfoil and the atmospheric conditions in which the airfoil is flying. Sound Wave Simulator allows you to explore the doppler effect and the formation of Mach waves. Interactive Nozzle Simulator solves the isentropic flow equations for the flow through a rocket nozzle, a converging- diverging turbine nozzle or a converging turbine nozzle. Shock Wave Simulator solves the flow equations for supersonic flow past a wedge. Input variables include the Mach number, and wedge angle. Multiple Shock Wave Simulator solves the flow equations for supersonic flow past multiple wedges. Input variables include the Mach number, wedge angles, and the spacing between the wedges. The icon at the top of each section will take you to a web page which contains a simulator or calculator for an aerodynamics problem. The web page assumes that you understand the problem and contains only the applet and a couple of hyperlinks to additional pages which describe the science and math behind each problem and some additional instructions on the program operation. The linked pages will take a little longer to load into your browser. If you follow the instructions provided you can download a copy of each program to your computer and you can then run the programs off-line.

University of Maryland: Alfred Gessow Rotorcraft Center

The Alfred Gessow Rotorcraft Center (AGRC) at the University of Maryland is one of three rotorcraft centers of excellence established by the Army Research Office (ARO) in 1982. The site provides access to a range of information including: news items, a list of the faculty and their research interests, and a description of the Center's facilities. The research interests of the Center include: rotor dynamics and smart structures; aerodynamics, active and passive damping control of smart structures; damage detection and health monitoring; CFD and acoustics; flight mechanics and controls; and composite structures. References to staff research papers are listed under some of the research sections. the website also as link to the award winning design of the AHS annual student design competion.

Virginia Tech : Experimental Fluid Dynamics Research

This site describes the experimental fluid dynamics research activities at Virginia Polytechnic Institute and State University, within the Aerospace and Ocean Engineering department. An area of particular interest is wing tip vortices and the site provides details of research projects in this area. There is a listing of papers produced by personnel within the department, a few of which are available in full text in PDF format. Experimental data and details of facilities and instruments is also made available.

Wall Interference, Support Interference and Flow Field Measurements

This is Research and Technology Organization (RTO) AGARD-CP-535, dated July 1994. The 31 papers prepared for the AGARD Fluid Dynamics Panel (FDP) Symposium on 'Wall Interference, Support Interference, and Flow Field Measurements' are contained in this report. In addition, a Technical Evaluator's Report assessing the success of the Symposium in meeting its objectives, and an edited transcript of the General Discussion held at the end of the meeting are also included. The primary objective of this Symposium was to report on recent developments from research and technology programs aimed at reducing test data errors caused by wind tunnel walls, model supports, and intrusive flow field measurement devices. The scope of papers included wall interference correction methods based on measured data at the walls and methods to eliminate wall interference through adaptive and/or ventilated walls, support interference calculations and correction methods, and recent advances in flow field measurement techniques. For individual titles, see N95-19252 through N95-19282. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (128.87MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

X-15 Research Results With a Selected Bibliography

This web site provides access to a NASA Dryden Flight Research Center history series publication, NASA SP-60, by Wendell H. Stillwell, 1964. This covers the history of the X-15 between 1959 and 1964, and was written halfway through the programme. It includes a chronology and bibliography. The full text is available online in HTML format.

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