Numerical solution of Space Shuttle Orbiter flow field including real gas effectsThe hypersonic, laminar flow around the Space Shuttle Orbiter has been computed for both an ideal gas (gamma = 1.2) and equilibrium air using a real-gas, parabolized Navier-Stokes code. This code employs a generalized coordinate transformation; hence, it places no restrictions on the orientation of the solution surfaces. The initial solution in the nose region was computed using a 3-D, real-gas, time-dependent Navier-Stokes code. The thermodynamic and transport properties of equilibrium air were obtained from either approximate curve fits or a table look-up procedure. Numerical results are presented for flight conditions corresponding to the STS-3 trajectory. The computed surface pressures and convective heating rates are compared with data from the STS-3 flight.
Document ID
19840056580
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Prabhu, D. K. (Iowa State Univ. of Science and Technology Ames, IA, United States)
Tannehill, J. C. (Iowa State University of Science and Technology, Ames, IA, United States)