Mach 5 inlet CFD and experimental results | Zendy

Lois J. Weir | Zendy; D. R. Reddy | Zendy; G. Rupp | Zendy

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Mach 5 inlet CFD and experimental results

Author(s) -

Lois J. Weir,

D. R. Reddy,

G. Rupp

Publication year - 1989

Publication title -

24th joint propulsion conference

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1989-2355

Subject(s) - computational fluid dynamics , mach number , inlet , mechanics , aerospace engineering , computer science , environmental science , mechanical engineering , engineering , physics

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.

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