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Numerical solution for unsteady sonic flow over thin wingsA numerical solution precedure of a simplified unsteady transonic equation which is fast, reasonably accurate, and takes into account many of the effects of the steady flow field is described. The numeric solution of this equation is accurate and is accomplished on an IBM 360/65 computer. Arbitrary planform shape is accommodated and variable local Mach number effects from the steady flow are easily handled.
Document ID
19750004827
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Kimble, K. R. (Tennessee Univ. Space Inst. Tullahoma, TN, United States)
Wu, J. M. (Tennessee Univ. Space Inst. Tullahoma, TN, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-141114
Accession Number
75N12899
Funding Number(s)
CONTRACT_GRANT: NGR-43-001-102
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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