Program uses method of characteristics for steady three-dimensional flow to calculate flow field in supersonic portion of mixed-compression aircraft inlet at non-zero angle of attack. Results agree well with experimental data except in regions of high viscous interaction. Flow field for variety of mixed-compression inlets can be calculated. Input includes geometry and attack of inlet. Output consists of list of parameters, solution planes, and description of shock waves. Program is written in FORTRAN IV for batch execution on CDC 6000-series.
Flow field in supersonic mixed-compression inlets
NASA Tech Briefs ; 5 , 1
1980-08-01
Miscellaneous
No indication
English
Quasi 1D Modeling of Mixed Compression Supersonic Inlets
British Library Conference Proceedings | 2012
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