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Analysis of leading edge separation using a low order panel methodAn examination of the potential flow computer code VSAERO to model leading edge separation over a delta wing is examined. Recent improvements to the code suggest that it may be capable of predicting pressure coefficients on the body. Investigation showed that although that code does predict the vortex roll-up, the pressure coefficients have significant error. The program is currently unsatisfactory, but with some additional development it may become a useful tool for this application.
Document ID
19890019122
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Sandlin, Doral R. (California Polytechnic State Univ. San Luis Obispo, CA, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-185892
NAS 1.26:185892
Accession Number
89N28493
Funding Number(s)
CONTRACT_GRANT: NCC2-226
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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