As a preliminary step toward predicting the leeside thermal environment for winged reentry vehicles at flight conditions, a computational solution for the flow about the Shuttle Orbiter at wind tunnel conditions was made using a point-implicit, finite volume scheme known as the Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA). The surface pressures resulting from the computational solution are compared with wind tunnel data. The results indicate that the dominant inviscid flow features are being accurately predicted on the leeside of the Shuttle Orbiter at a moderately high angle of attack.
High Angle of Attack Inviscid Shuttle Orbiter Computation
1992
23 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Aerodynamics , Fluid Mechanics , Aerothermodynamics , Angle of attack , Hypersonic flow , Inviscid flow , Space shuttle orbiters , Computational fluid dynamics , Finite volume method , Algorithms , Computation , Computational grids , Mach number , Pressure distribution , Reentry vehicles , Wind tunnel tests