Abstract
The object of this paper is to describe an accurate and efficient numerical procedure to compute the supersonic inviscid flow field about complicated three-dimentional aircraft configurations and to demonstrate how the technique works in a practical case. A two level second order marching scheme is used to integrate Euler's equations in regions where the flow is continuous. Shocks are, however, treated explicitly as descontinuities satisfying the Renkine-Hugoniot equations. Use is made of conformal mappings in order to provide proper resolution in critical areas. Results are presented for several three-dimentional flow field computations including a complete aircraft and the results are compared with experiments.
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