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.


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