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A computer program for the calculation of the flow field including boundary layer effects for mixed-compression inlets at angle of attackA computer program was developed which is capable of calculating the flow field in the supersonic portion of a mixed compression aircraft inlet operating at angle of attack. The supersonic core flow is computed using a second-order three dimensional method-of-characteristics algorithm. The bow shock and the internal shock train are treated discretely using a three dimensional shock fitting procedure. The boundary layer flows are computed using a second-order implicit finite difference method. The shock wave-boundary layer interaction is computed using an integral formulation. The general structure of the computer program is discussed, and a brief description of each subroutine is given. All program input parameters are defined, and a brief discussion on interpretation of the output is provided. A number of sample cases, complete with data listings, are provided.
Document ID
19830002796
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Vadyak, J. (Purdue Univ. West Lafayette, IN, United States)
Hoffman, J. D. (Purdue Univ. West Lafayette, IN, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1982
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-168002
NAS 1.26:168002
Accession Number
83N11066
Funding Number(s)
PROJECT: RTOP 505-32-12
CONTRACT_GRANT: NSG-3311
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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