Supersonic external compression inlets are introduced, and the computational fluid dynamics (CFD) codes and tests needed to study flow associated with these inlets are outlined. Normal shock wave turbulent boundary layer interaction is discussed. Boundary layer control is considered. Glancing sidewall shock interaction is treated. The CFD validation of hypersonic inlet configurations is explained. Scramjet inlet modules are shown.
CFD application to supersonic/hypersonic inlet airframe integration
1988-01-01
Conference paper
No indication
English
Novel inlet–airframe integration methodology for hypersonic waverider vehicles
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