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Large perturbation flow field analysis and simulation for supersonic inletsAn analysis technique for simulation of supersonic mixed compression inlets with large flow field perturbations is presented. The approach is based upon a quasi-one-dimensional inviscid unsteady formulation which includes engineering models of unstart/restart, bleed, bypass, and geometry effects. Numerical solution of the governing time dependent equations of motion is accomplished through a shock capturing finite difference algorithm, of which five separate approaches are evaluated. Comparison with experimental supersonic wind tunnel data is presented to verify the present approach for a wide range of transient inlet flow conditions.
Document ID
19870001402
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Varner, M. O. (Sverdrup Technology, Inc. Arnold AFS, TN, United States)
Martindale, W. R. (Sverdrup Technology, Inc. Arnold AFS, TN, United States)
Phares, W. J. (Sverdrup Technology, Inc. Arnold AFS, TN, United States)
Kneile, K. R. (Sverdrup Technology, Inc. Arnold AFS, TN, United States)
Adams, J. C., Jr. (Sverdrup Technology, Inc. Arnold AFS, TN, United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:174676
NASA-CR-174676
Accession Number
87N10835
Funding Number(s)
CONTRACT_GRANT: NAS3-23682
PROJECT: RTOP 505-43-42
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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