A pair of numerical methods for predicting the flow past hypersonic vehicle configurations that include wings, fins, flaps, and a propulsion system, are described. The governing equations and fundamental details of the solution methods are reviewed. Results for both geometrically simple test cases and realistic hypersonic configurations are given. Since there is still a considerable lack of experience for hypersonic flow calculations, extensive testing and verification are essential. This verification is done by comparison of results with experimental data and other numerical methods. The results presented prove that the methods used are robust, flexible, and accurate enough to fulfill the needs of the design process.
Numerical Methods for Aerothermodynamic Design of Hypersonic Space Transport Vehicles
1992
16 pages
Report
No indication
English
Manned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Aerodynamics , Aerothermodynamics , Boundary layer equations , Design analysis , Euler equations of motion , Hypersonic vehicles , Navier-stokes equation , Spacecraft design , Aerodynamic configurations , Computational fluid dynamics , Flow distribution , Grid generation (Mathematics) , Hypersonic flow , Space transportation system , Thermodynamics , Foreign technology