高超声速飞行的若干气动问题

doi:10.7527/S1000-6893.2014.0224

Abstract

Abstract:

Transition, laminar flow separation and aerodynamic error band are some aerodynamic issues which should be paid more attention to for hypersonic flight. The aerodynamic properties may be influenced obviously and with some uncertainty by transition and laminar flow separation. And how to determine the aerodynamic error band reasonably is also a key for hypersonic flight. These issues and their influences are discussed in this paper mainly from the view point of engineering design. To fulfill the need of hypersonic flight, we should further develop the relevant theoretical analysis and digital simulation technology and raise the technical level of ground tests at wind tunnel. Besides, aerodynamic flight tests should also be emphasized.

Key words: hypersonic, aerodynamic design, transition, flow separation, aerodynamic error band

CLC Number:

V411

YU Ping, DUAN Yi, CHEN Jun. Some aerodynamic issues in hypersonic flight[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(1): 7-23.

References

[1] Wagnild R M. High enthalpy effects on two boundary layer disturbances in supersonic and hypersonic flow[D]. Minneapolis, MN: The University of Minnesota, 2012.
[2] An M Y, Wang K C, Campbell C H, et al. Space shuttle orbiter aerodynamics induced by asymmetric boundary-layer transition, AIAA-1996-0808 [R]. Reston: AIAA, 1996.
[3] Juliano T J . Instability and transition on the HIFiRE-5 in a Mach-6 quiet tunnel[D]. Washington, D.C.: Purdue University, 2006.
[4] Odam J, Paull A, Alesi H, et al. HIFiRE-0 flight test data, AIAA-2009-7293 [R]. Reston: AIAA, 2009.
[5] Kimmel R L, Adamczak D W. HIFiRE-1 preliminary aerothermodynamic measurements (postprint), AFRL-RB-WP-TP-2012-0197[R]. Ohio: AFRL, 2012.
[6] Li F, Meelan C, Chang C L, et al. Transition analysis for the HIFiRE-1 flight experiment, AIAA-2011-3414[R]. Reston: AIAA, 2011.
[7] Kimmel R, Adamczak D, Gosse R, et al. Ground test and computation of boundary layer transition on the hypersonic international flight research and experimentation (HIFiRE)-5 vehicle, AFRL-RB-WP-TR-2011-3025[R]. Ohio: AFRL, 2011.
[8] Choudhari M, Chang C L, Thomas J, et al. Transition analysis for the HIFiRE-5 vehicle, AIAA-2009-4056 [R]. Reston: AIAA, 2009.
[9] Borg M P, Kimmel R L, Stanfield S. Traveling crossflow instability for HIFiRE-5 in a quiet hypersonic wind tunnel, AIAA-2013-2717[R]. Reston: AIAA, 2013.
[10] Chen F J, Berry S A. HyBoLT flight experiment, NASA/TM-2010-216725[R]. Washington, D.C.: NASA, 2010.
[11] Horvath T M, Berry S A, Merski N R, et al. X-38 experimental aerothermodynamics, AIAA-2000-2685[R]. Reston: AIAA, 2000.
[12] Baiocco P. Pre-X experimental re-entry lifting body: design of flight test experiments for critical aerothermal phenomena[R]. Evry Cedex: Center National D'Etudes Spatiales, 2007.
[13] Holden M S. Historical review of experimental studies and prediction methods to describe laminar and turbulent shock wave/boundary layer interactions in hypersonic flows, AIAA-2006-0494[R]. Reston: AIAA, 2006.
[14] Vandomme L, Chanetz B, Benay R, et al. Shock wave/transitional boundary-layer interactions in hypersonic flow, AIAA-2003-6966[R]. Reston: AIAA, 2003.
[15] Holden M S, Wadhams T P, Candler G V. Experimental studies in the LENS shock tunnel and expansion tunnel to examine real-gas effects in hypervelocity flows, AIAA-2004-0916[R]. Reston: AIAA, 2004.
[16] Holden M S, Wadhams T P, Smolinski G J, et al. Experimental and numerical studies on hypersonic vehicle performance in the LENS shock and expansion tunnels, AIAA-2006-0125[R]. Reston: AIAA, 2006.
[17] Wadhams T P, Holden M S. Summary of experimental studies for code validation in the LENS facility and comparison with recent Navier-Stokes and DSMC solutions for two- and three-dimensional separated regions in hypervelocity flows, AIAA-2004-0917[R]. Reston: AIAA, 2004.
[18] Rockwell International. Aerodynamic design data book—Volume 1M: Orbiter vehicle STS-1, NASA-CR-160903[R]. Washington, D.C.: NASA, 1980.
[19] Morelli E A, Derry S D, Smith M S. Aerodynamic parameter estimation for the X-43A (Hyper-X) from flight data, AIAA-2005-5921[R]. Reston: AIAA, 2005.
[20] Young J C, Underwood J M. Development of aerodynamic uncertainties for the space shuttle orbiter[J]. Journal of Spacecraft, 1983, 20(6): 513-517.
[21] Cobleigh B R. Development of the X-33 aerodynamic uncertainty model, NASA/TP-1998-206544[R]. Washington, D.C.: NASA, 1998.

Some aerodynamic issues in hypersonic flight

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