The combination of increased computer power and fast numerical codes have led to a situation that the flow field around a complete reentry vehicle can be computed in approximately half a day. This allows the use of complex CFD tools in the design procedure of future spacecraft.

This seminar will discuss the physical and chemical phenomena which have to be considered in the development of a CFD code for hypersonic, high enthalpy flows. Also, the basis of modern high resolution shock capturing schemes will be outlined. A very important step in the development of a new scheme is its validation which can only be achieved through a close cooperation with wind tunnel experiments.

Finally an overview of results will be given which have recently been obtained with the numerical codes developed at the German Aerospace Research Establishment (DLR) in the framework of the European Space Program.