Integrating CFD and Experiment in Aerodynamics - CFD4Aircraft

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the experiment, to perform the measurements, it requires a solid background in fundamental fluid mechanics. The database constitution is not limited to the acquisition of a vast amount of results, but must be accompanied by an in depth analysis of the flow physics. Because of the investment needed by such operations and their strategic importance for the development of predictive methods, the question of the database test cases dissemination inevitably arises. It is now realised that a good database can be as precious as a code and cannot be freely transmitted. Even basic experiments have now an economic weight and cannot be put on the market without something in exchange. Thus, dissemination rules have to be more precisely defined according to the more or less precious nature of the database contents. In addition of the permanent scientific concern about more accurate, safer and less expansive predictive methods, the problem of the constitution of valuable, safe, well identified and permanent databases is now considered as a strategic issue and addressed seriously. In this perspective, the ONERA Fluid Mechanics and Energetic Branch has started the constitution of a database containing the most prominent experimental results obtained in its research wind tunnels of the Meudon-Centre over the last 30 years 38 . This task will be actively pursued and the database contents fed with new experiments satisfying the quality criteria here above defined. At the European level, the ERCOFTAC association has constituted a database containing 82 test cases, stored by the University of Surrey, which can be obtained through the ERCOFTAC website 39 . In the framework of the FLOWNET European-Union project a database has been constituted which can be accessed through the INRIA website 40 . Thus, several national and international initiated have been initiated in the past years to build complete, well documented and safe databases in order to help in the development of accurate predictive methods both for research end industry. Concluding Remarks The confidence in code predictions is still limited because of the uncertainties in the numerical handling of the equations and of the lack of accuracy of the physical models implemented in the codes. This is particularly true in separated high Mach number flows which contain both intense shock waves, thin shear layers, separated regions (laminar, transitional and turbulent) and are affected by real gas effects. A consequence of the intense development of the CFD activity has been to urge experimentalists to execute more complete experiments, including the definition of all the flow properties. This demand has motivated an important effort to develop advanced and non intrusive methods for detailed flow investigation, such as PSP, infrared thermography, LDV, DGV, laser spectroscopic diagnostic techniques, etc. Thus, during the past years a strategy has emerged to organise more efficiently the dialectics between computation and experiment. To validate their codes, numericians need an as complete as possible information on some representative test cases. This information constitutes what is called a database which must respect certain rules to be useful. Thus, the database must contain a precise description of the configuration, along with all the necessary flow and boundary conditions. The measurements must be considered as safe, and if possible accurate, these objectives being difficult to reach in hypersonic facilities because of the extreme flow conditions and the short useful test duration. Uncertainty margins must be provided in order to allow meaningful conclusion on the accuracy of physical models. Bibliography 1. Roache, P.J., Verification of Codes and Calculations, AIAA Journal, Vol. 36, N°5, May 1998, pp. 696-702 2. The ERCOFTAC Best Practice Guidelines for Industrial Computational Fluid Dynamics. Contact ahhutton@qinetic.com 3. Benay, R., Chanetz, B. and Délery, J., Code Verification/Validation with Respect to Experimental Data Banks, Aerospace Science and Technology, 7 (2003), pp. 239-362 4. Délery, J. and Chanetz, B., Experimental Aspects of Code Verification/Validation: Application to Internal Aerodynamics, VKI Lecture Series 2000-08, 5-8 June, 2000 5 Bur,R., Corbel, B. and Délery, J., Study of Passive Control in a Transonic Shock Wave/Boundary Layer Interaction. AIAA Journal, Vol. 36, N°3, 1998, pp. 394- 400 6 Chanetz, B., Benay, R., Bousquet, J.-M., Bur, R., Pot, T., Grasso, F. and Moss, J., Experimental And Numerical Study of the Laminar Separation in Hypersonic Flow, Aerospace Science and Technology, No. 3, 1998, pp. 205-218 7 Schneider, S.P.,Rufer, S.J., Randall, L. and Skoch, C., Shakedown of the Purdue Mach-6 Quiet-Flow Ludwieg Tube, AIAA Paper 2001-0457, Jan. 2001 8 Van Dyke, M., An Album of Fluid Motion, The Parabolic Press, Stanford, CA,1982 9. Délery, J., Robert Legendre and Henri Werlé: Toward the Elucidation of Three-Dimensional Separation, Ann. Rev. Fluid Mech.,2001-33, pp. 129- 154 10. Crites, R. C., Pressure Sensitive Paint Technique, VKI Lecture Series 1993-05 on Measurement Techniques, April 1993 11. Mébarki, Y., Peintures sensibles à la pression : application en soufflerie aérodynamique (Pressure Sensitive Paints: Application in wind tunnels). Ph. D. Dissertation, University of Lille 1, March 1998 12
12. Mébarki, Y. and Mérienne, M. C., PSP Application on a Supersonic Aerospike Nozzle, PSP Workshop, Seattle, USA, Oct. 6-8, 1998 13 Settles, G. S., Recent Skin-Friction Techniques for Compressible Flows, AIAA Paper 86-1099, May 1986 14 Seto, J. and Hornung, H., Two-Directional Skin Frictions Measurement Utilizing a Compact Internally- Mounted Thin-Liquid Skin-Friction Meter; AIAA Paper 93-0180, Jan. 1993 15 Desse, J. M., Oil-Film Interferometry Skin-Friction Measurements under White Light. AIAA Journal, Vol. 41, N°4, April 2003 16 Bouchardy, A. M, Durand, G. and Gauffre, G., Processing of Infrared Thermal Images for Aerodynamics Research, 1983 SPIE Int. Technical Conference, Geneve, April 18-22, 1983 17 Gartenberg, E. and Roberst, S. Jr., Twenty-Five Years of Aerodynamics Research with Infrared Imaging, Thermosense XIII, SPIE Proc. Vol. 1467, 1991, pp. 338- 353 18 Le Sant, Y. and Fontaine, J., Application of Infrared Measurements in the ONERA's Wind Tunnels, Wind Tunnels and Wind Tunnel Test Techniques, Cambridge, U.K., April 14-16, 1997 19 Yanta, W.-J., Turbulence Measurements with a Laser Doppler Velocimeter, NOLTR 73-94, 1973. 20 Boutier, A., Caractérisation de la turbulence par vélocimétrie laser (Turbulence Characterization with Laser Velocimetry) 35 ème Colloque d'Aérodynamique Appliquée de l'AAAF, Lille, France, March 22-24, 1999 21 Boutier, A. and Micheli, F., Laser Anemometry for Aerodynamics flow Characterization, La Recherche Aérospatiale, N°3, 1996, pp. 217-226 22 Meyers, J. F., Development of Doppler Global Velocimetry for Wind Tunnel Testing, 18 th Aerospace Ground Testing Conference, Colorado Springs, CO, June 1994, AIAA Paper 94-2582 23 Lempereur, C., Barricau, P., Mathe, J. M. and A. Mignosi, Doppler Global Velocimetry: Accuracy Test in a Wind Tunnel, ICIASF 99, Toulouse, France, June 14- 17, 1999 24 Samimy, M. and Wernet, M. P., Review of Planar Multiple-Component Velocimetry in High Speed Flows, AIAA Journal, Vol. 38, N°4, April 2000 25 Riethmuller, M. L., Vélocimétrie par images de particules ou PIV. Summer school of the Association Francophone de Vélocimétrie Laser, Saint-Pierre d'Oléron, Sept. 22-26, 1997 26 Raffel, M., Willert, C. and Kompenhans, J., Particle image velocimetry. A practical guide. Springer-Verlag, 1998 27 Beck, W. H., Trinks, O. and Mohamed, A., Diode Laser Absorption Measurements in High Enthalpy Flows: HEG Free Stream Conditions and Driver Gas Arrival, 22 nd International Symposium on Shock Waves, Imperial College, London, U.K., July 18-23, 1999 28 Chanetz, B., Bur, R., Dussillols, Joly, V., Larigaldie, S., Lefèbvre, M., Marmignon, C., Mohamed, A. K., Oswald, J., Pot, T., Sagnier, P., Vérant, J. L. and William, J., High Enthalpy Hypersonic Project at ONERA, Aerospace Science and Technology, Vol. 4, N°5, July 2000, pp. 347-361 29 Lefebvre, M., Chanetz, B., Pot, T., Bouchardy, P. and Varghese, Ph., Measurement by Coherent Anti- Sokes Raman Scattering in the R5Ch Hypersonic Wind Tunnel, Aerospace Research, No. 1994-4, 1994, pp. 295-298. 30 Grisch, F., Bouchardy, P., Péalat, M., Chanetz, B., Pot, T. and Cöet, M.-C., “Rotational Temperature and Density Measurements in a Hypersonic Flow by Dualline CARS”, Applied Physics B 56, 1993, pp. 14-20 31 Gross, K.-P., McKenzie, R.-L. and Logan, P., Measurements of Temperature, Density, Pressure, and Their Fluctuations in Supersonic Turbulence Using Laser-Induced Fluorescence, Experiments In Fluids 5, 1987, pp. 372-380 32 Hiller, B. and Hanson, R.-K., Simultaneous Planar Measurements of Velocity and Pressure Fields in Gas Flows using Laser-Induced Fluorescence, Applied Optics, Vol. 27, N°1, Jan. 1988, pp. 33-48 33 Mohamed, A.K., Pot, T. and Chanetz, B., Diagnostics by Electron Beam Florescence in Hypersonics, 16 th International Congress on Instrumentation in Aerospace Facilities, Dayton, OH, July 18-21, 1995 34 Kuznetsov, L., Rebrov, A. and Yarigin, V., Diagnostics of Ionized Gas by Electron Beam in X-Ray Spectrum Range, 11 th Int. Conference on Phenomena in Ionized Gases, Prague, 1973 35 Gorchakova, N., Kuznetsov, L., Rebrov, A. and Yarigin, V., Electron Beam Diagnostics of High Temperature Rarefied Gas, 13 th Int. Symposium on Rarefied Gas Dynamics - Vol. 2, Plenum Press Eds., 1985, pp. 825-832 36 Gorchakova, N., Chanetz, B., Kuznetsov, L., Pigache, D., Pot, T., Taran, J.-P. and Yarigin, V., Electron Beam Excited X-Ray Method for Density Measurements of Rarefied Gas Flows Near Models. 21 st Int. Symposium on Rarefied Gas Dynamics - Vol. 2, Cepadues Eds., Toulouse, France, July 1999, pp. 617- 624 37 Larigaldie, S., Bize, D., Mohamed, A. K., Ory, M., Soutadé, J. and Taran, J. P., Velocity Measurement in High Enthalpy, Hypersonic Flows using an Electron Beam Assisted Glow Discharge, AIAA Journal, Vol. 36, N°6, June 1998 38 Benay, R., La base de données du DAFE. Mise à jour 2001 (The Data Bank of the Fundamental/ Experimental Aerodynamics Department. Update 2001), ONERA Technical Report N° RT 3/03589 DAFE, July 2001 39 ERCOFTAC Database at University of Surrey at www.ercoftac.org 40 FLOWNET Database at INRIA at www.inria.fr 13
Page 1 and 2: Integrating CFD and Experiment in A
Page 3 and 4: Experimentalist’s requirements fo
Page 5 and 6: persistent discrepancy may be due t
Page 7 and 8: numbers significantly lower than th
Page 9 and 10: Heat flux measurements. Over the pa
Page 11 and 12: The measurements are made on select
Page 13: advantage that the signal is emitte
Page 17 and 18: castellated nozzles entrained more
Page 19 and 20: Axisymmetric Regular Convergent Div
Page 21 and 22: Figure 5: Typical instantaneous PIV
Page 23 and 24: Figure 8: Streamwise Velocity Profi
Page 25 and 26: 1.25 CFD (SKW PRESTO) Experimental
Page 27 and 28: 5 Conclusions In this paper we have
Page 29 and 30: 2 which include boundary layer and
Page 31 and 32: 4 not received much attention in th
Page 33 and 34: 6 Although a great deal of effort h
Page 35 and 36: 8 Computational simulations can con
Page 37 and 38: 10 separation location over rounded
Page 39 and 40: 12 3.7 Vortex / flexible wing inter
Page 41 and 42: 14 [8] Mitchell, A.M. and Molton, P
Page 43 and 44: 16 [31] Gursul, I., Proposed Mechan
Page 45 and 46: 18 Figure 3: Spectrum of unsteady f
Page 47 and 48: 20 Figure 7: Flow visualisation of
Page 49 and 50: Figure 11: Upper surface pressure d
Page 51 and 52: While the information presented in
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Cs comparison at V=0.6 m/s Fig. 10.
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Investigation of Flow Turning in a
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Figure 1. Natural Blockage Thrust R
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Figure 7. Post-Exit rake Total Span
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Figure 11. Comparison of Static Pre
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2.2 Data Aquired The Embedded Laser
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First, plots of the turbulent Reyno
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Particles seeding tube 3 m 1 m mode
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Figure 5: Influence of the pseudo t
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Figure 7: Turbulent Reynolds' numbe
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Figure 9: Turbulent Reynolds' numbe
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Figure 11: Vortex Shedding cycle fo
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Figure 13: Comparison with experime
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