CALCULATION OF SUPERSONIC FLOW AROUND AXISYMMETRIC FLARES
TRW SPACE TECHNOLOGY LABS LOS ANGELES CALIF
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A machine program for the computation of supersonic flow around an axisymmetric flare is described. The computation consists of the following parts 1 The oblique shock problem in which upstream flow properties vary with position. 2 Calculation of the initial shock angle at the compression corner. 3 Insertion of characteristics for uniformity of mesh size.