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 3-dimensional parabolized Navier-Stokes (PNS) and 3D full NavierStokes (FNS) analytical codes. Analytical predictions and experimental results are compared.
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