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CFD Simulation of the Space Shuttle Launch Vehicle with Booster Separation Motor and Reaction Control System Plumes

  • L. M. Gea
  • D Vicker

Summary

The primary objective of this paper is to demonstrate the capability of computational fluid dynamics (CFD) to simulate a very complicated flow field encountered during the space shuttle ascent. The flow field features nozzle plumes from booster separation motor (BSM) and reaction control system (RCS) jets with a supersonic incoming cross flow at speed of Mach 4. The overset Navier-Stokes code OVERFLOW [1], was used to simulate the flow field surrounding the entire space shuttle launch vehicle (SSLV) with high geometric fidelity. The variable gamma option was chosen due to the high temperature nature of nozzle flows and different plume species. CFD predicted Mach contours are in good agreement with the schlieren photos from wind tunnel test. Flow fields are discussed in detail and the results are used to support the debris analysis for the space shuttle Return To Flight (RTF) task.

Keywords

Computational Fluid Dynamic Computational Fluid Dynamic Simulation Space Shuttle Wind Tunnel Test Oblique Shock 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. 1.
    Buning, P.G., et al., OVERFLOW Use’s Manual, Version 1.8j, February 1999.Google Scholar
  2. 2.
    Columbia Accident Investigation Board Report, August 2003.Google Scholar
  3. 3.
    Buning, P.G., et al., Flow field Simulation of the Space Shuttle Vehicle in Ascent, Proc. Fourth International Conference on Supercomputing, April 1989.Google Scholar
  4. 4.
    Buning, P.G., Chiu, I.T., Obayashi, S., Rizk, Y.M., and Steger, J.L., Numerical Simulation of the Integrated Space Shuttle Vehicle in Ascent, AIAA-88-4359-CP, August 1988.Google Scholar
  5. 5.
    Slotnick, J.P., Kandula, M., Buning, P.G., and Martin, F.W., Numerical Simulation of the Space Shuttle Vehicle Flow Field with Real Gas Solid Rocket Motor Plume Effects, AIAA-93-0521, January 1993.Google Scholar
  6. 6.
    Gomez, R.J. and Ma, E.C., Validation of a Large Scale Chimera Grid System for Space Shuttle Launch Vehicle, AIAA-94-1859, August 1994.Google Scholar
  7. 7.
    Suhs, N.E., Dietz, W.E., Nash, S.M., Onufer, J., Baker, D., and Rogers, S.E., PEGAUS User’s Guide Version 5.1c, July 2000.Google Scholar
  8. 8.
    Smith, S.D., High Altitude Chemical Reaction Gas Particle Mixture Code User’s Manual, NAS9-16256, 1984.Google Scholar
  9. 9.
    Spalart, P.R., and Allmaras, S.R., A One-Equation Turbulence Model for Aerodynamic Flows, AIAA 92-0439, AIAA paper 92-0439, January 1992.Google Scholar
  10. 10.
    Crosby, W. A. and Lanham, D. D., Integrated aerodynamic tests of the space shuttle vehicle during solid rocket booster separation at Mach 4.5 (IA193), NASA Center for Aerospace Information, AEDC-TSR-82-V15, June 1982.Google Scholar
  11. 11.
    Marroquin, J. and Lemoine, P., Results of wind tunnel tests of an ASRM configured 0.03 scale Space Shuttle integrated vehicle model (47-OTS) in the AEDC 16-foot transonic wind tunnel, NASA Center for Aerospace Information, NASA-CR-185697, October 1992.Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2006

Authors and Affiliations

  • L. M. Gea
    • 1
  • D Vicker
    • 2
  1. 1.The Boeing CompanyHuntington Beach
  2. 2.EG3-Applied AeroscienceNASA Johnson Space CenterHouston

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