Several solutions for the internal flow in axisymmetric supersonic inlets at angle of attack were obtained. A shock-capturing finite-difference technique was used to obtain the solutions. Good overall agreement between the shock-capturing solutions and experimental data was obtained, except in regions of strong viscous effects or boundary-layer removal. The required centerbody translation with changes in freestream Mach number and angle of attack was obtained and agrees qualitatively with experimental data.
Internal flow calculations for axisymmetric supersonic inlets at angle of attack
Propulsion Conference ; 1975 ; Anaheim, CA
1975-09-01
Conference paper
No indication
English
Internal flow calculations for axisymmetric supersonic inlets at angle of attack
Tema Archive | 1975
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