This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Shock Wave Formation and Aerodynamic Heating in the Presence of a Protrusion on Flat Plate in High Speed Flow
Technical Paper
2010-01-1830
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
Protruding objects from the surface of space orbiters induce aerodynamic heating at transonic to hypersonic speeds. The gap-filler material which came loose from between the insulation tiles on the surface of the space orbiter Discovery during its reentry is a case in point. The interaction between the protruding gap filler and the boundary layer may drastically alter the flow field at high speeds, resulting in formation of shock waves and aerodynamic heating of the walls. A CFD was carried out on a two-dimensional model of the flow over a gap-filler like protrusion attached to a flat wall representing the obiter surface. The flow was at speeds corresponding to three different orbiter Mach numbers of 2.54, 1.5 and 0.64 depending on the altitude. The flow and temperature fields were solved numerically. The computations indicated the formation of shock waves upstream and downstream of the gap filler and higher wall temperatures were noticed due to viscous dissipation effects. The maximum wall temperature at Mach number of 2.54 was 231°C, indicating 282°C overheating above the free stream temperature at an altitude of 25 km. Analysis of the results indicated the serious thermal impact of protruding objects on surfaces in high speed flow.
Authors
Citation
Khan, N., "Shock Wave Formation and Aerodynamic Heating in the Presence of a Protrusion on Flat Plate in High Speed Flow," SAE Technical Paper 2010-01-1830, 2010, https://doi.org/10.4271/2010-01-1830.Also In
References
- http://www.nasa.gov/pdf/124112main_msg075.pdf
- http://www.stanford.edu/group/ctr/about.html
- Truitt, R. W. 1960 Fundamentals of Aerodynamic Heating Ronald Press Co. NY
- Oosthuizen, P. H. Carscallen, W. E. 1997 Compressible Fluid Flow McGraw-Hill Co.
- Panton, R. L. 1984 Incompressible Flow John Wiley & Sons
- Pope, S. B. 2000 Turbulent Flows Cambridge University Press
- “Landing the Space Shuttle Orbiter” NASA Technical Facts Sheet FS-2000-05-30-KSC Kennedy Space Center
- Stalder, J. R. Rubesin, M. W. Tendeland, T. 1950 “A determination of the Laminar-, Transitional-, and Turbulent-Boundary-Layer Temperature Recovery Factors on Flat Plate in Supersonic Flow” NACA Technical Note 2077
- Allen, H. J. Eggers, A. G. Jr. “A study of the Motion and Aerodynamic Heating of Ballistic Missiles entering the Earth's Atmosphere at Supersonic Speeds” NACA Technical Report 1381
- Spalart, P. R. Allmaras, S. R. “A one-equation turbulence model for aerodynamic flows” AIAA Paper 92-0439
- Paciorri, R. Dieudonne, W. Degrez, G. Charbonnier, J. M. Deconick, H. “Validation of the spalart-allmaras turbulence model for application in hypersonic flows” AIAA 1997
- Thivet, F. “Lessons learned from RANS simulations of Shock Wave Boundary Layer-Interaction (SWBLI)” AIAA 2002-0583
- US Standard Atmosphere 1976 U.S Government Printing Office Washington D.C. August 2005
- Shapiro, A. H. 1954 The Dynamics and Thermodynamics of Compressible Fluid Flow II The Ronald Press Co. New York
- http://www.cfd-online.com/Wiki
- Fluent Inc. FLUENT 6.3 Users Guide Lebanon, NH