Computation of flow past aerospace vehicles

This paper describes the simulation of compressible flow past complex aeros pace geometries, using Computational Fluid Dynamics (CFD), The computations have been done using a cell vertex-based finite volume scheme and structur ed multi-block grids. Results are described for the viscous flow past a cro pped delta wing, where the flow simulation is able to explain some of the c omplex fluid flow phenomena. Results are also shown for inviscid flow past multi-body launch vehicle configurations and an aircraft configuration. The se simulations of the flow past realistic aerospace configurations show tha t CFD can now play an important role in the design and development of such vehicles.