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Bleed-boundary conditions for numerically simulated mixed-compression supersonic inlet flowA numerical study was performed to investigate boundary conditions for bleed openings that are needed in the numerical simulation of critical flow through turbojet inlets with bleed. Nine different boundary conditions (BCs) were devised and examined. Of the BCs examined, three were able to stabilize the terminal shock near the inlet's throat. This numerical study was based on the ensemble-averaged, unsteady, three-dimensional, compressible Navier-Stokes equations closed by the Baldwin-Lomax algebraic turbulence model. Solutions to the Navier-Stokes equations were obtained by using a hybrid implicit-explicit method (Beam and Warming/MacCormack). The multiblock grid system used in the solution procedure was generated by solving a set of elliptic partial differential equations. Solutions obtained were compared with available experimental data.
Document ID
19920061896
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Chyu, W. J.
(NASA Ames Research Center Moffett Field, CA, United States)
Howe, G. W.
(NASA Ames Research Center Moffett Field, CA, United States)
Shih, T. I-P.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 15, 2013
Publication Date
August 1, 1992
Publication Information
Publication: Journal of Propulsion and Power
Volume: 8
Issue: 4, Ju
ISSN: 0748-4658
Subject Category
Aerodynamics
Accession Number
92A44520
Distribution Limits
Public
Copyright
Other

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