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A user's guide for V174, a program using a finite difference method to analyze transonic flow over oscillating wingsThe design and usage of a pilot program using a finite difference method for calculating the pressure distributions over harmonically oscillating wings in transonic flow are discussed. The procedure used is based on separating the velocity potential into steady and unsteady parts and linearizing the resulting unsteady differential equation for small disturbances. The steady velocity potential which must be obtained from some other program, is required for input. The unsteady differential equation is linear, complex in form with spatially varying coefficients. Because sinusoidal motion is assumed, time is not a variable. The numerical solution is obtained through a finite difference formulation and a line relaxation solution method.
Document ID
19780004070
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Butler, T. D. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Weatherill, W. H. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Sebastian, J. D. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Ehlers, F. E. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-145214
Accession Number
78N12013
Funding Number(s)
CONTRACT_GRANT: NAS1-14204
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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