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Comparison of 3-D viscous flow computations of Mach 5 inlet with experimental dataA time marching 3-D full Navier-Stokes code, called PARC3D, is validated for an experimental Mach 5 inlet configuration using the data obtained in the 10 x 10 ft supersonic wind tunnel at the NASA Lewis Research Center. For the first time, a solution is obtained for this configuration with the actual geometry, the tunnel conditions, and all the bleed zones modeled in the computation. Pitot pressure profiles and static pressures at various locations in the inlet are compared with the corresponding experimental data. The effect of bleed zones, located in different places on the inlet walls, in eliminating the low energy vortical flow generated from the 3-D shock-boundary layer interaction is simulated very well even though some approximations are used in applying the bleed boundary conditions and in the turbulence model. A further detailed study of the effect of individual bleed ports is needed to understand fully the actual mechanism of efficiently eliminating the vortical flow from the inlet. A better turbulence model would help to improve the accuracy even further in predicting the corner flow boundary layer profiles.
Document ID
19900010774
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Reddy, D. R.
(Sverdrup Technology, Inc., Cleveland OH., United States)
Benson, T. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Weir, L. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1990
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.15:102518
NASA-TM-102518
E-5322
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Reno, NV
Country: United States
Start Date: January 8, 1990
End Date: January 11, 1990
Sponsors: AIAA
Accession Number
90N20090
Funding Number(s)
PROJECT: RTOP 505-62-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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