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Fluid mechanics - fluid dynamics

A Simple, Robust and Fast Algorithm to Compute Deformations of Multi-Block Structured Grids

This technical report (NLR-TP-2002-105) was published by NLR (the National Aerospace Laboratory of the Netherlands) in 2002 and was written by S. P. Spekreijse, B. B. Prananta and J. C. Kok. A grid deformation method has been developed for the movement of multiblock, structured grids due to surface deformation arising from aeroelastics or design optimisation. The method uses a volume spline interpolation technique to compute the deformation of block vertices and block edges. After that, the deformation of block-faces is computed by an arclength-based two-dimensional transfinite interpolation method. Finally, an arclength-based three-dimensional transfinite interpolation method is used to compute the deformation of grid points inside the blocks. The method is demonstrated for simple and complex aeroelastic aircraft applications using Navier-Stokes computational fluid dynamics. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Advances In Computational Fluid Dynamics : Turbulent Separated Flows And Transonic Potential Flows

This site provides access to a Virginia Polytechnic Institute and State University Department of Aerospace and Ocean Engineering PhD dissertation, by Reece E. Neel, dated 6 June 1997. The dissertation presents computational solutions to flows ranging from incompressible viscous flows to inviscid transonic flows. The viscous flow problems focus on turbulence modeling in the presence of separation; and the inviscid results focus on the development of an unstructured solution algorithm. Bibliographic and abstract details are available in HTML format. The full text of the document is accessible online in PDF format [3.51 Mb]. This title is part of Virginia Tech's Electronic Thesis and Dissertation Collection (VT ETD).

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.

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.

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.

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.

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.

Cargo Compartment Smoke Transport Computational Fluid Dynamics Code Validation

This technical report (DOT/FAA/AR-07/27) was produced by the Federal Aviation Administration (FAA) in July 2007 and was written by Jill Suo-Anttila, Walt Gill, Anay Luketa-Hanlin and Carlos Gallegos. A computational model designed to predict smoke and gas transport within aircraft cargo compartments has been validated for potential use in the certification process of cargo compartment fire detection systems. The simulations and experiments compared herein represent a spectrum of scenarios that provide confidence in the models’ ability to predict the transport of smoke and combustion products in a variety of conditions. The main variables that changed between the cases were fire location, compartment size, and ventilation. Validation metrics suitable for fire detection system response were selected and, overall, the model favorably predicted these metrics for the selected cases. The model can now be used with improved confidence to simulate certification scenarios of interest to assist in designing the optimum detection systems for cargo compartments. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software is required in order to read it.

CFD Investigation of Effect of Depth to Diameter Ratio on Dimple Flow Dynamics

This is the full text of a thesis written by Robert Etter, which was presented to the Air Force Institute of Technology, Wright Patterson Air Force Base, Ohio in June 2007. This study aimed to further the understanding of laminar flow through a dimple with the goal of mitigating flow separation. Dimples of various depth to diameter ratios (0.05, 0.15) were examined for three different dimple diameters and chordwise locations, corresponding to diameter based (ReD) and chordwise location based (Rex) Reynolds number combinations of ReD 20500\Rex 5000, ReD 20500 Rex 77000, and ReD 9000 Rex 21000. For the last combination, a dimple of depth to diameter ratio of 0.25 was also examined. The dimples were placed in a flat plate located in a diverging channel causing an adverse pressure gradient encouraging flow separation near the dimple location. The flow was modeled in the commercial CFD solver Fluent. Results indicate that dimple depth to diameter ratio has a significant effect on the structure of dimple flow. The shallowest dimples showed little change to the overall flow in the channel. Deeper dimples contained dynamic vortical flow structures with behavior varying between each dimple studied. This dynamic vortex activity was observed to be linked with variances in downstream flow. The 0.15 depth to diameter ratio dimples showed behavior very similar to 0.10 ratio dimples investigated elsewhere. The 0.25 dimple show flow different in nature than 0.15 dimples for the same ReD and Rex; the differences were not as stark as those between 0.05 and 0.15 dimples. In light of this and other studies, dimple flow behavior is found to depend on a combination of parameters that eludes direct quantitative parameterization. However, the conclusion is drawn that the most effective dimple will be just deep enough to develop dynamic vortical activity and vortex shedding. [Taken from abstract]. This is in PDF format so Adobe Acrobat software is required in order to read it.

Concepts NREC

The company is a turbomachinery design and development organization providing all the resources required to develop complete solutions from concept through detailed engineering, product design, prototype production, performance testing and product manufacturing. The products developed by Concepts NREC cover the entire range of turbomachinery applications and markets including aerospace, military and commercial aviation, ground support, power generation, petrochemical and process equipment, refrigeration, biomedical, automotive, marine, and agriculture. The site contains descriptions of the company's products and services, and provides details of job opportunities, news and events. Copies of the Company's newsletter, SpinOffs, can be accessed online. Concepts NREC is also involved in education and training and a section of the site describes the company's courses and publications, including a number of turbomachinery handbooks and textbooks. An online bookstore is available for ordering purposes. The site also provides access to the full text of a select collection of Concepts NREC technical papers in PDF format, covering topics such as optimization, and the design of axial flow and centrifugal compressors and turbines.

Fluid Dynamics Problems of Vehicles Operating Near or in the Air-Sea Interface

This site provides access to a Research and Technology Organization Meeting Proceedings, RTO-MP-015, Paris, February 1999. The document contains papers presented at the RTO Applied Vehicle Technology Panel (AVT) Symposium (organised by the former AGARD Fluid Dynamics Panel), held in Amsterdam, The Netherlands, 5-8 October 1998. Topics covered at the symposium included aerodynamics and flight dynamics around ships, stabilization and control techniques for ships, and non-classical aircraft flying near the air-sea interface. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (46.2 Mbytes) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library

Fluid Dynamics Research on Supersonic Aircraft

This web page provides access to a Research and Technology Organization (RTO) educational note, RTO-EN-004, dated November 1998. The publication contains lecture notes from a RTO Applied Vehicle Technology Panel (AVT) Special Course on "Fluid Dynamics Research on Supersonic Aircraft", held at the von Karman Institute for Fluid Dynamics (VKI) in Rhode-Saint-Genese, Belgium, 25-29 May 1998. A number of topics are covered including: history and economics of supersonic transports; supersonic aerodynamics; sonic boom theory and minimization; multi-point design challenges; vortex plume interactions; and propulsion system design. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text of the document (52.8 Mbytes) can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Institute of Fluid Science, Tohoku University

The Institute conducts research on flow science in areas such as development of low-intrusive medical treatments with shock waves, creation of advanced technology for better utilization of natural energy sources, development of manufacturing processes of new materials, development of high-functionality material / fluid systems, and advancement of high-efficiency supersonic flight and space propulsion technology. The site describes in detail the research that it undertakes and also provides the Fluid Science Database, a searchable and browseable database of full text papers from the Institute.

Internal Aerodynamics in Solid Rocket Propulsion

This is a Research and Technology Organization (RTO) Educational Note, RTO-EN-023, Paris, January 2004. The material in this publication was assembled to support a RTO/VKI Special Course under the sponsorship of the Applied Vehicle Technology Panel (AVT)and the von K�rm�n Institute for Fluid Dynamics (VKI) presented on 27-31 May 2002 in Rhode-Saint-Gen�se, Belgium. These RTO-AVT/VKI Special Course notes provide the state of the art in internal aerodynamics in solid rocket propulsion, in a way accessible to attendees coming from both academic and industrial areas. Two families of solid motors can be identified: tactical rockets and large boosters for launch vehicles. The military rockets are subjected to combustion instabilities while vortex shedding drives the instabilities in the large boosters. After an overview of the motor internal flow dynamics, combustion of solid propellants and metal particulates were presented. Numerical modeling of internal flow aerodynamic, two-phase flow and flow/structural interactions were addressed, before focusing on the motor flow and combustion instabilities. Bibliographic and abstract details are available in HTML format. A table of contents, individual papers and the full text of the document (18.6 Mbytes) can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Measurement Techniques for High Enthalpy and Plasma Flows

This web site provides access to a Research and Technology Organization (RTO) educational note, RTO-EN-008, dated April 2000. The publication contains papers presented at the Applied Vehicle Technology Panel (AVT), held at the von Kármán Institute for Fluid Dynamics (VKI) in Rhode-Saint-Genèse, Belgium, 25-29 October 1999. A number of topics were covered including: high enthalpy and plasma flow facilities; intrusive and non-intrusive measurement techniques for the characterization of flows; and utilization of the plasma facilities for the evaluation of material catalytic properties. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text of the document (45.3 Mbytes) can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Measurements of the Tip-gap Turbulent Flow Structure in a Low-speed Compressor Cascade

This is a Virginia Polytechnic Institute and State University Department of Aerospace and Ocean Engineering PhD dissertation, by Genglin Tang, dated April 9, 2004. This dissertation presents results from a thorough study of the tip-gap turbulent flow structure in a low-speed linear compressor cascade wind tunnel. The most complete data sets were acquired for 1.65% and 3.30% tip gap/chord ratios. The study found that tip gap flows are complex pressure-driven, unsteady three-dimensional turbulent flows. Bibliographic and abstract details are available in HTML format. The full text of the document is accessible online in PDF format [40.38 Mb]. This title is part of Virginia Tech�s Electronic Thesis and Dissertation Collection (VT ETD)

Non Linear Dynamics and Chaos

This is Research and Technology Organization (RTO) AGARD-LS-191, dated June 1993. Many efforts were oriented towards the understanding of the unexpected behavior of systems - linear or non-linear. These could be large (weather systems, biological life) or small (automatic pilot). A new branch of dynamics is now considered; it is called 'chaos'. Some general theories emerged and reconsideration of concepts of non-linear control to determine the stability of such systems is now intensively studied in the scientific community. The following topics are covered: linear (including time varying coefficients equations) vs non-linear systems; types of non-linearity; curved characteristics, jumps, bifurcation; nonlinear dynamics; sensibility to initial conditions and/or uncertainties on the system parameters; robustness; neuronal-type machines; chaos - random process behavior; reversibility; irreversibility; Newtonian mechanics and thermodynamics; fractals; and applications. For individual titles, see N94-18237 through N94-18241. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (19.60MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Numerical Prediction Capabilities and Analysis of Flow Development for a Supersonic Civil Transport at Low Speed

This technical report (NLR-TP-2002-496) was published by NLR (the National Aerospace Laboratory of the Netherlands) in 2002 and was written by J. Van Muijden and A. Elsenaar. This paper focuses on two issues. First, it describes the application of present-day multi-block structured CFD-tools to the analysis of flow development and prediction of aerodynamic coefficients of a supersonic civil transport (SCT) with leading-edge flap deflections at low-speed conditions. Second, the flow development with incidence and separation onset is studied to obtain a better understanding of the type of flow under consideration. The numerical study of the flow around this configuration is based on solution of the Navier-Stokes equations in combination with a two-equation k-? turbulence model employing specific modifications for vortex-dominated flow. The flow conditions examined range between 6 and 12 degrees incidence, at a Mach number of 0.25 and a Reynolds number of 7.3 million, based on mean aerodynamic chord. Different meshes have been used to assess the dependency of flow solutions on mesh density. Comparison with experimental data and industrial accuracy requirements is performed, from which indications for minimum mesh density are derived. The study of flow development with incidence is based on experimental oil flow patterns, pressure distributions and aerodynamic coefficients, supplemented with flow field and surface data from the CFD-solutions. It is concluded that the low-speed aerodynamic characteristics for attached as well as separated flow on an SCT with deflected leading-edge flaps can be predicted with acceptable accuracy, in accordance with industrial accuracy requirements. This allows the presented method to be applied in further computational studies regarding the improvement of low-speed characteristics of SCT. [Taken from abstract]. The full text is available as a PDF file.

Reduced Order Modeling for High Speed Flows with Moving Shocks

This is the full text of a thesis by David J. Lucia which was presented to the Air Force Institute of Technology (AFIT) in 2002. The use of Proper Orthogonal Decomposition (POD) for reduced order modeling (ROM) of fluid problems is extended to high-speed compressible fluid flows. The challenge in using POD for high-speed flows is presented by the presence of moving discontinuities in the flow field. To overcome these difficulties, a domain decomposition approach is developed that isolates the region containing the moving shock wave for special treatment. The domain decomposition implementation produces internal boundaries between the various domain sections. The domains are linked using optimization-based solvers which employ constraints to ensure smoothness in overlapping portions of the internal boundary. This approach is applied to three problems with increasing difficulty. The ability of POD/ROM to model a high-speed quasi 1-D nozzle flow is analyzed first. The quasi 1-D nozzle contains a standing shock which is moved in a quasi-steady manner by varying the ratio of specific heats (�). Next, reduced order modeling for quasi-steady shock motion in a two-dimensional high-speed flow is studied. A 2-D blunt body flow containing a strong bow shock is the subject of this analysis. The bow shock is moved by varying boundary parameters. Lastly, the approach is applied to a transonic aeroelastic problem that involves large motions of a normal shock. 2-D inviscid flow over an elastic panel produces transonic limit cycle oscillations under certain panel parameters and free stream conditions. Panel flutter in the transonic regime results in the large motion of a transonic normal shock across the panel surface. Previously, no reduced order modeling method has been successfully applied to this problem. [Taken from abstract]. The full text of the thesis is available in PDF format and is provided by the Air University ResearchWeb site.

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.

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 Unstructured Grid Methods for Advection Dominated Flows

This is Research and Technology Organization (RTO) AGARD-R-787 , dated May 1992. Lecture notes for the AGARD Fluid Dynamics Panel (FDP) Special Course on 'Unstructured Grid Methods for Advection Dominated Flow' have been assembled in this report. The objective of this course was to provide state of the art information, as well as recent developments in unstructured grid methods, suitable for the computation of high Reynolds number compressible and incompressible flows, and other related subjects. A wide range of applications is presented, which includes incompressible free surface problems, transonic aerodynamics, and hypersonic reentry flows. For individual titles, see N92-27672 through N92-27680. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (56.05MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Technology Requirements for Small Gas Turbines

This is Research and Technology Organization (RTO) AGARD-CP-537, dated March 1994. These Conference Proceedings contain the papers presented at the Propulsion and Energetics Panel 182nd Symposium on Technology Requirements for Small Turbines which was held from 4th-8th October 1993, in Montreal, Canada. The Technical Evaluation Report and the Technology Overview Address are included at the beginning, and discussions follow most papers. The Symposium was arranged in the following Sessions: Technology Overview; Turboshaft Engines; Turbofan Engines; Auxiliary Power Units; Compressors 1 - Centrifugal; Compressors 2 - Axial; Combustors; Turbines 1 - Axial; Turbines 2 - Radial; Structures and Materials; and Bearings. For individual titles, see N94-34432 through N94-34466. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (31.57 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 Role of Instability in Gaseous Detonation

This is a California Institute of Technology, Graduate Aeronautical Laboratories PhD dissertation, by Joanna Maria Austin, submitted May 21st, 2003. In detonation, the coupling between fluid dynamics and chemical energy release is critical. The reaction rate behind the shock front is extremely sensitive to temperature perturbations and, as a result, detonation waves in gases are always unstable. A broad spectrum of behavior has been reported for which no comprehensive theory has been developed. The problem is extremely challenging due to the nonlinearity of the chemistry-fluid mechanics coupling and extraordinary range of length and time scales exhibited in these flows. Past work has shown that the strength of the leading shock front oscillates and secondary shock waves propagate transversely to the main front. A key unresolved issue has emerged from the past 50 years of research on this problem: What is the precise nature of the flow within the reaction zone and how do the instabilities of the shock front influence the combustion mechanism? In the study this issue has been examined through dynamic experimentation in two facilities. Key diagnostic tools include unique visualizations of superimposed shock and reaction fronts, as well as short but informative high-speed movies. A range of fuel-oxidizer systems, including hydrocarbons are studied, and these mixtures are broadly categorised by considering the hydrodynamic stability of the reaction zone. Bibliographic and abstract details are available in HTML format. The full text of the document is accessible online in PDF format [65.87 Mb]. This title is part of California Institute of Technology's Electronic Thesis and Dissertation (ETD) Collection

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.

University of Southampton School of Engineering Sciences : Aerodynamics and Flight Mechanics

This group is engaged in leading-edge research in fundamental fluid dynamics, computational aeroacoustics, applied aerodynamics and flight dynamics. Specific areas of research are industrial aerodynamics, high speed flows, fluid mechanics, applied aerodynamics and aeroacoustics and rotorcraft design and aircraft operations. The site describes research projects and facilities, provides information on staff and students including publications, and links to e-Prints Soton for full text publications.

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.

Von Karman Institute for Fluid Dynamics

The von Karman Institute is a non-profit international educational and scientific organisation, hosting three departments (aeronautics and aerospace, environmental and applied fluid dynamics, and turbomachinery & propulsion). It provides post-graduate education in fluid dynamics (Research Master in Fluid Dynamics, doctoral program, stagiaire program and lecture series) and encourages "training in research through research". Established in 1956, following Theodore von Kármán's proposal, for the training and research in aerodynamics of young scientists and engineers of the Nato nations, it is currently supported with subsidies from most of the member countries of NATO and with an income derived from contract research. This website describes the educational programs and publications available, research carried out by staff and students within the different departments and provides links to other sites including an extensive CFD (computational fluid dynamics) resource section.

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.

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