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Unsteady Aerodynamics for Advanced Configurations: Part II - A Transonic Box Method for Planar Lifting Surfaces

Report Number: FDL TDR 64-152 Part 2
Author(s): E. R. Rodemich; L. V. Andrew
Corporate Author: North American Aviation, Incorporated
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1965-05
Pages: 128
Contract: AF 33(657)-10399
Project: 1370
Task: 137003
AD Number: AD0618097

The fundamental equations of the transonic box method were derived, based on the representation of the velocity potential by a doublet distribution. They form the basis of a systematic method of treating an oscillating wing at M = 1, analogous to the supersonic Mach box method. A digital computer program, written in Fortran IV, is presented. The program applies to a planar wing of polygonal planform, with a straight trailing edge, and as many as three sweep angles along the leading edge. For a maximum of ten modes of oscillation, the program computes the oscillatory potentials and pressures and a generalized force matrix. Results obtained from the program are compared with existing theoretical and experimental values. Several possible extensions of the method are described.

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