Application of a finite difference method to the analysis of transonic flow over oscillating airfoils and wingsA finite difference method for solving the unsteady flow about harmonically oscillating wings is investigated. The procedure is based on separating the velocity potential into steady and unsteady parts and linearing the resulting unsteady differential equation for small disturbances. Solutions are obtained using relaxation procedures. The means for improving the solution stability characteristics of the relaxation process are explored. A direct procedure is formulated which permits obtaining solutions for combinations of Mach number and reduced frequency for which the relaxation process has proved unstable. The pressure distribution for an aspect ratio 5 rectangular wing oscillating in pitch is presented.
Document ID
19770024146
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Weatherill, W. H. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Sebastian, J. D. (Boeing Computer Services Inc., Seattle, United States)
Ehlers, F. E. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Date Acquired
August 8, 2013
Publication Date
April 1, 1977
Publication Information
Publication: AGARD Unsteady Airloads in Separated and Transonic Flow