A three dimensional fully viscous computer analysis was evaluated to determine its usefulness in the design of supersonic inlets. This procedure takes advantage of physical approximations to limit the high computer time and storage associated with complete Navier-Stokes solutions. Computed results are presented for a Mach 3.0 supersonic inlet with bleed and a Mach 7.4 hypersonic inlet. Good agreement was obtained between theory and data for both inlets. Results of a mesh sensitivity study are also shown.
Numerical simulation of supersonic inlets using a three-dimensional viscous flow analysis
Aerospace Sci. Meeting ; 1980 ; Pasadena, CA, United States
1980-01-01
Conference paper
No indication
English
Numerical Simulation For Supersonic Inlets
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