Code development for hypersonic realgas flow simulations toward the design of space vehicles
Abstract
Hypersonic flows over simple three dimensional bodies and a practical plane are simulated using a real gas NavierStokes code under an equilibrium air assumption. This code is based on three dimensional upwind flux splitting scheme with generalized Roe's Riemann solver. The real gas effect is incorporated using the Variable Equivalent Gamma (VEG) method. The equivalent gamma and other thermodynamic properties are calculated using empirical curve fits of equilibrium air. Numerical simulations are conducted for flow fields around a spherical blunt body, a hemisphere, as simple configurations, and H2 Orbiting PlanE (HOPE: Japanese spaceplane) as a practical plane configuration. Flow conditions are Mach numbers of 7.72 for hemisphere, 15.0 for the blunt bodies and HOPE. Computed pressure and density distributions are presented. Results for simple configuration case is compared with experimental data for the code validation.
 Publication:

In NAL
 Pub Date:
 December 1991
 Bibcode:
 1991acca.proc..129N
 Keywords:

 Blunt Bodies;
 Computational Fluid Dynamics;
 Digital Simulation;
 Hypersonic Flow;
 Hypersonic Vehicles;
 Three Dimensional Flow;
 Density Distribution;
 Flow Distribution;
 Mach Number;
 NavierStokes Equation;
 Pressure Distribution;
 Temperature Distribution;
 Tvd Schemes;
 Spacecraft Design, Testing and Performance