Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations, Mach Number Range 1.5 to 2.0
1957
38 pages
Report
No indication
English
Aerodynamics , Angle of attack , Free stream , Inlet flow , Supersonic flow , Bleed , Boundary layer , Distortion , Flow , Free , Fuselage , High angle , Inlet , Internal , Mach number , Pressure , Ramp , Recovery , Stability , Stream , Supersonic , Throat , Zero