A detailed description of the procedure used to compute three dimensional, supersonic, inviscid, steady flows past airframes is given. No limitations are imposed on the geometry of the airplane. Suitable computational grids are generated by automatic conformal mappings. The equations of motion, with pressure, entropy, and velocity direction as basic unknowns, are written and discretized in the computational space. Special rules to approximate derivatives are given. Boundary points are treated by a modified method of characteristics.
Calculation of the three-dimension, supersonic, inviscid, steady flow past an arrow-winged airframe, part 1
1976-05-01
Report
No indication
English
Inviscid Supersonic Far Wake Flow past Pointed Bodies
AIAA | 1974
|Calculation of inviscid supersonic flow over ablated nosetips
Tema Archive | 1979
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