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Aerodynamic configurations

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.

Accurate Computation of Drag for a Wing/Body Configuration Using Multi-Block, Structured-Grid CFD Technology

This technical report (NLR-TP-2001-321) was published by NLR (the National Aerospace Laboratory of the Netherlands) in 2001 and was written by O. J. Boelens, M. Laban, C. M. van Beek and R. van der Leeden. In this report the contribution of the National Aerospace Laboratory NLR to the 'CFD Drag Prediction Workshop' organized by the AIAA in Anaheim, CA, on June 9-10, 2001, is presented. This contribution consists of both the results of all test cases and a discussion on the accurate computations of drag coefficients. Two approaches are presented and discussed. The first method performs a grid convergence study using a sequence of nested grids yielding the grid-converged drag coefficient. To enable this study to be carried out, such a sequence of nested multi-block structured grids ('NLR' grid) has been generated. The second method, using one grid only, decomposes the drag coefficient into its 'physical components' (vortex, wave and viscous drag). As a consequence, this method provided the aerodynamic designer with a helpful tool, because of its diagnostic potential. [Taken from abstract]. The full text is available as a PDF file.

Aerodynamic Analysis of The Joined-Wing Configuration of A High-Altitude, Long Endurance (HALE) Aircraft

This web site provides access to a University of Cincinnati, Department of Mechanical Engineering and Engineering Mechanics MS dissertation, by Rangarajan Sivaji, dated May 2004. The three-dimensional, unsteady, flow is simulated over the joined-wing section of a HALE (High-Altitude Long Endurance) aircraft based on the Sensorcraft configuration. This is the first step in the high-fidelity, nonlinear aeroelastic analysis of the HALE aircraft. The flow solution is obtained by solving the Reynolds-Averaged Navier-Stokes (RANS) governing equations, using the Spalart-Allmaras turbulence model, or by using Detached Eddy Simulation (DES). With successful completion of the validation cases, simulations were performed at the lower and upper limits of the operating regime of the Sensorcraft. Inviscid simulations were also considered as a computationally efficient alternative to viscous simulations for the computation of the surface pressure loads to be applied on the structure, particularly at low angle of attack. This is verified by performing inviscid simulations, and comparing the resulting pressure with the corresponding viscous results at the Mach number of 0.6. The study serves as the foundation to provide an integrated aerodynamic and structural analyses software using a Multi-Disciplinary Computing Environment (MDICE) to predict the aeroelastic behavior of lifting bodies. Bibliographic and abstract details are available in HTML format. The title page, contents and the full text of the document are accessible online in PDF format (7.19 Mb). This title is part of the OhioLINL Electronic Theses and Dissertations Project.

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 Modeling Using Computational Fluid Dynamics and Sensitivity Equations

This web site provides access to a Virginia Polytechnic Institute and State University Department of Aerospace and Ocean Engineering PhD dissertation, by Alejandro Cesar Limache, dated 10 April 2000. The dissertation presents a mathematical model for the determination of aerodynamic forces, based on the generalisation of the idea of aerodynamically steady motions. Computer codes have been developed to obtain numerical solutions for airfoils moving in general steady motions. These are used to to calculate variation of the lift, drag and pitching moment with respect to the pitch rate at different mach numbers and angles of atttack. Bibliographic and abstract details are available in HTML format. The full text of the document is accessible online in PDF format [9.36 Mb]. This title is part of Virginia Tech's Electronic Thesis and Dissertation Collection (VT ETD).

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.

Analytical Services and Materials Inc : PAB3D Software

The web site describes the computer software PAB3D for the analysis of propulsion components and propulsion airframe integration. PAB3D solves the three-dimensional Reynolds-averaged Navier-Stokes equations with a finite-volume formulation on structured multi-block grids. The site describes key features of the software, and various technnology applications including: nozzle internal performance, external aerodynamics, fluidic thrust vectoring, and high NPR axisymmetric supercruise. The site also provides access to PAB3D documentation and supporting publications, and has an online request facility for ordering the software (including licence fees).

Calculation of Unsteady Subsonic and Supersonic Flow about Oscillating Wings and Bodies by New Panel Methods

This technical report (NLR-TP-89119) was published by NLR (the National Aerospace Laboratory of the Netherlands) in 1989 and was written by M. H. L. Hounjet. Unsteady aerodynamic loads in the subsonic and supersonic domain have been obtained with two new panel methods for lifting surfaces and for realistic aircraft configurations. A description of the methods is given. Results are presented and comparisons are made with results of existing methods and with experimental data for a fighter-type wing with external stores. [Taken from abstract]. The full text is available as a PDF file.

Computational Fluid Dynamics Investigation of Vortex Breakdown for a Delta Wing at High Angle of Attack

This is the full text of a thesis by Jacob A. Freeman which was presented to the Air Force Institute of Technology (AFIT) in 2003. Using the commercially available FLUENT 3-D flow field solver, this research effort investigated vortex breakdown over a delta wing at high angle of attack (a) in preparation for investigation of active control of vortex breakdown using steady, alongcore blowing. A flat delta-shaped half-wing with sharp leading edge and sweep angle of 60° was modeled at a = 18° in a wind tunnel at Mach 0.04 and Reynolds number of 3.4 x 105. A hybrid (combination of structured and unstructured) numerical mesh was generated to accommodate blowing ports on the wing surface. Results for cases without and with along-core blowing included comparison of various turbulence models for predicting both flow field physics and quantitative flow characteristics. FLUENT turbulence models included Spalart-Allmaras (S-A), Renormalization Group k-e, Reynolds Stress (RSM), and Large Eddy Simulation (LES), as well as comparison with laminar and inviscid models. Mesh independence was also investigated, and solutions were compared with experimentally determined results and theoretical prediction. These research results show that, excepting the LES model for which the computational mesh was insufficiently refined and which was not extensively investigated, none of the turbulence models above, as implemented with the given numerical grid, generated a solution which was suitably comparable to the experimental data. Much more work is required to find a suitable combination of numerical grid and turbulence model. [Taken from abstract]. The full text of the thesis is available in PDF format and is provided by the Air University ResearchWeb site.

Drag Estimates for the Joined-Wing Sensor Craft

This is the full text of a Master's thesis by Ensign Ryan L. Craft, USN, AFIT/GAE/ENY/05-J02, which was presented to the Faculty Department of Aeronautics and Astronautics of Air University's Air Force Institute of Technology, in June 2005. This research studied the drag effects of the joined-wing sensor craft technology demonstrator being developed at the Air Force Research Laboratory (AFRL). Although many performance parameters have been studied and evaluated for this vehicle, to date no detailed drag estimates have been conducted for the AFRL configuration. Previous performance parameters of the aircraft have been estimated based solely on a constant lift-to-drag ratio assumption. Using the Air Vehicles Technology Integration Environment created by Dr. Maxwell Blair, and supplemented by MATLAB code, this study explored three different drag prediction methods to determine accurate estimates of both parasite and induced drag. The Roskam/AVTIE Pan Air method was determined as the best approach to estimate drag by measuring parasite drag effects using XFOIL, a respected environment within the aviation industry to accurately predict all viscous drag effects, and determined induced drag from Pan Air, a creditable software package based on inviscid flow field solutions about three-dimensional objects. This method will be incorporated into a single design environment, in conjunction with AVTIE, to estimate drag and aid future AFRL joined-wing design studies incorporating wing twist, aeroelastic effects, and other geometric changes to the baseline configuration. [Taken from abstract]. The full text is available in PDF format on the Scientific and Technical Information Network (STINET) which is provided by the Defense Technical Information Center (DTIC).

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.

Experimental data base for computer program assessment: Report of the Fluid Dynamics Panel Working Group 04

This is Research and Technology Organization (RTO) AGARD-AR-138, dated January 1979. The acquisition of highly reliable wind tunnel test data for aircraft design was investigated. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (16.7MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Experimental Study of the Subsonic Aerodynamics of a Blended Wing Body Air Vehicle with a Focus on Rapid Technology Assessment

This is the full text of a Master's thesis by Second Lieutenant David A Gebbie, USAF, AFIT/GAE/ENY/05-M09, which was presented to the Faculty Department of Aeronautics and Astronautics of Air University's Air Force Institute of Technology (AFIT), in March 2005. The subsonic aerodynamic performance of a blended wing body aircraft constructed using selective laser sintering was assessed in the AFIT low-speed wind tunnel. The scaled-down model of a strike tanker aircraft consisted of a shaped fuselage and sweptback wings. The Reynolds number, based on mean wing chord, during testing was on the order of 105 while the Mach number ranged from 0.10 to 0.20. The model evaluation and analysis process included force and moment measurements acquired from a wind tunnel balance, pressure data measured with 8 taps located on the model's upper surface, a comparison to computational fluid dynamics (CFD) solutions acquired in a parallel study conducted by AFRL/VAAC, and global pressure sensitive paint (PSP) measurements. Paint measurements were compared to pressure tap data to ensure their accuracy while lift and drag coefficients, as well as pitching and rolling moments were examined to determine performance characteristics, including stability attributes and aircraft stall. One of the most interesting results was the striking difference in the force and moment measurements before and after the paint was applied to the surface. The average surface roughness, Ra, was measured with a profilometer and was found to have increased from approximately 0.3μm to 0.7μm when the paint was applied. When traditional 2-D boundary layer approaches to assessing the effect of roughness, the 0.7μm value falls well below the threshold at which one would anticipate roughness to have any effect. There is support in archival literature for the notion that roughness effects are more pronounced in a 3-D boundary layer, and the pitching moment data and the PSP data indicate that the for the painted model, there is a gradual onset of wing stall marching inward from the wingtips toward the body. [Taken from abstract]. The full text is available in PDF format on the Scientific and Technical Information Network (STINET) which is provided by the Defense Technical Information Center (DTIC).

FanWing : A Revolution in Flight Technology

This site is from FanWing Ltd, a company that specialises in designing fan wings. These lift and thrust a plane by employing a wing with a cross-flow fan at the leading edge. The quietness and stability of the flight achieved lends its application to remotely piloted vehicles (RPVs), ultra/microlight weight aircrafts, surveillance, local taxi services and freight haulage. The site provides background information to the technology and includes pictures, photographs and video and audio footage (requiring Windows Media Player) of several flying models.

Flight Test Measurement Techniques for Laminar Flow

This is Research and Technology Organization (RTO) AGARDograph, RTO-AG-300-V23, edited by D. Fisher, K.H. Horstmann and H. Riedel; sponsored by the Flight Test Technology Team (FT3) of the Systems Concepts and Integration Panel (SCI) of RTO, dated October 2003. This AGARDograph provides information on flight test techniques, instrumentation, environmental effects, and flight procedures that have been used successfully in laminar flow research. Many techniques are described for measuring the location of boundary layer transition in-flight, from the very simple to the more complex. References to previous works are included for readers to explore. Specific instrumentation for flight is described and the unique environmental effects of flight noted. Procedures for flight test maneuvers are also included. Techniques discussed cover both local and global measurements. Some of the local flow techniques include surface temperatures, hot-film and hot-wire anemometry, raised-pitot, and traversing surface pitot. Global flow techniques include the infrared imaging, oil flow, liquid crystal, sublimating chemicals, and emitted fluid techniques. Some of the environmental concerns discussed include atmospheric particulate (ice crystals) and turbulence. Flight test procedures for infrared imaging and for insect contamination avoidance are described. Bibliographic details and an abstract are available in HTML format. The full text can be accessed online in PDF format (103 Mb) from the RTO's web site.

Hanley Innovations

This is a US company that provides aerodynamics and airfoil analysis software. The site provides software that can be downloaded for a fee in the following areas - airfoil analysis, wing analysis and scientific graphing. The site also provides a download of an electronic book entitled "Aerodynamics in plain English". Several full text articles are available in HTML format. A free newsletter is offered upon registration which gives updates on new products, upgrades, news and discounts.

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.

Human Consequences of Agile Aircraft

This web site provides access to a NATO Research and Technology Organization document titled: Human Consequences of Agile Aircraft, RTO-EN-012, March 2000. The report presents a number of papers presented as part of a lecture series. It evaluates the human factors implications for pilots of superagile flight, with specific reference to agile airframes and rapidly configurable systems. The citation and abstract information is in HTML format, and the full text is available online in PDF format (8 Mbytes).

Inverse Aerodynamic Shape Design for Improved Wing Buffet-Onset Performance

This technical report (NLR-TP-2000-150) was published by NLR (the National Aerospace Laboratory of the Netherlands) in 2000 and was written by B. I. Soemarwoto, Th. E. Labrujere, M. Laban and H. Yansyah. The paper describes the re-design of a wing/fuselage aircraft configuration in transonic flow with the objective to improve the buffet onset boundary in terms of lift coefficient CL at a cruise mach number of 0.8. This re-design is done by prescribing a pressure distribution on the wing surface that implies a higher CL at the buffet-onset boundary. The inverse problem refers to the computation of a wing shape that procedures the prescribed pressure distribution. A defect correction approach is applied for solving the re-design problem, where an inverse design methodology for isolated wings in inviscid flow is combined with viscous flow analysis code for wing/body configurations. The defect correction makes use of the design code SYN87 for isolated wings in inviscid flow and the analysis code MATRICS-V for wing/fuselage configuration in viscous flow. Computational results are shown for improvement of the buffet-onset performance of a wing/fuselage configuration at the design Mach number of 0.8. [Taken from abstract]. The full text is available as a PDF file.

Leading Edge Vortex Flow Computations and Comparison with DNW-HST Wind Tunnel Data

This technical report (NLR-TP-2001-238) was published by NLR (the National Aerospace Laboratory of the Netherlands) in 2001 and was written by F. J. Brandsma, J. C. Kok, H. S. Dol and A. Elsenaar. Computations are presented for the vortical flow around a sharp-edged cropped delta wing with 65 degree leading edge sweep using a computational method based on the Reynolds-averaged Navier-Stokes equations. It is demonstrated that turbulence modelling plays a crucial role in the ability to capture the vortical structures. Standard one- and two-equation turbulence models need corrections for vortical flows in order to avoid over-prediction of the levels of turbulent viscosity inside vortex cores. In this paper two types of modifications to the two-equation k-omega turbulence model are investigated to overcome this problem. One modification consists of limiting the production of turbulent kinetic energy in the k-equation, whereas the other modification is aimed at increasing the production of dissipation in the dissipation equation (omega equation); omega represents the dissipation of turbulent kinetic energy. The computational results at the conditions are compared with detailed experimental surface and field data obtained from a series of wind tunnel tests in the DNW-HST at NLR. The comparisons show that the modification which increases the production term for the dissipation rate of turbulent kinetic energy in the omega-equation produces the best results when it comes to capturing the vortex core in a realistic way. The proposed modification is in line with other approaches found in the literature for one-equation turbulence models. [Taken from abstract]. The full text is available as a PDF file.

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.

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.

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.

Recent Advances in Long Range and Long Endurance Operation of Aircraft

This is Research and Technology Organization (RTO) AGARD-CP-547, dated November 1993. Over the past few years, the use of aircraft in long range and/or long endurance operations has proved to be a successful use of military resources. Technologies which improve the range and endurance of aircraft have seen considerable advances over the past ten years. Aircraft design for these features has matured considerably while the procedure of air-to-air refuelling has made global deployment and 24+ hour operations a reality. This Symposium attempted to summarize the latest technological advances in the various fields which in a combined manner define the range and endurance of airborne vehicles, i.e.: airframe design technologies, including aerodynamic structures; propulsion technology; the human factors problems associated with these types of missions; and air-to-air refuelling technologies and procedures. For individual titles, see N94-36322 through N94-36347. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (77.16MB) 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.

Structural Stability of a Joined-Wing Sensorcraft

This is the full text of a thesis by Brandon\J.Adams USN, which was presented to the Air Force Institute of Technology, Wright-Patterson Air Force Base, Ohio in June 2007. This thesis employed a multi-disciplinary design approach to determine the structural stability of the Boeing Joined-Wing SensorCraft. Specifically, this thesis sought to characterize the free vibration modes, ensure a buckling safe design and determine the influence of the geometric and aeroelastic nonlinearities associated with this joined-wing design. The clamped free vibration modes were developed for a wind tunnel model and were compared to the free-free vibration modes, several differences were found. Linear static analyses were performed on numerous maneuver loads and gust conditions to determine the critical loading condition. The SensorCraft was then redesigned for the critical load case to be both panel and global buckling safe. The multi-disciplinary design process which incorporated both geometric nonlinearities and aeroelastic follower-force effects was then performed for the pre-gust trim and critical gust conditions. The resulting analysis showed that the deformations that resulted from the aerodynamic forces were not substantial enough to fully characterize the follower force effect. Furthermore this thesis demonstrates that the geometric and aeroelastic nonlinearities are not significant. However, for a fully optimized design incorporation of these coupled nonlinearities is critical. [Taken from abstract]. The full text is available in PDF format and is provided by the Defense Technical Information Center (DTIC)'s Scientific and Technical Information Network (STINET).

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.

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