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    Mach 5 inlet CFD and experimental results (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental research program was conducted in the NASA Lewis Research Center 10 ft. by 10 ft. supersonic wind tunnel. The two-dimensional inlet model was designed to study the Mach 3.0 to 5.0 speed range for an 'over-under' turbojet plus ramjet propulsion system. The model was extensively instrumented to provide both analytical code validation data as well as inlet performance information. Support studies for the program include flow field predictions with both three-dimensional parabolized Navier-Stokes (PNS) and three-dimensional full Navier-Stokes (FNS) analytical codes. Analytical predictions and experimental results are compared.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-2355
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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