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Title
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Unsteady Aerodynamics for Advanced Configurations: Part II - A Transonic Box Method for Planar Lifting Surfaces
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Date
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1965
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Index Abstract
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Coming Soon
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Photo Quality
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Not Needed
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Report Number
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FDL TDR 64-152 Part 2
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Creator
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Rodemich, E. R.
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Andrew, L. V.
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Corporate Author
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North American Aviation, Incorporated
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Laboratory
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Air Force Flight Dynamics Laboratory
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Extent
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128
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Identifier
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AD0618097
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Access Rights
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Notice(s)
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Distribution Classification
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1
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Contract
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AF 33(657)-10399
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DoD Project
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1370
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DoD Task
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137003
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DTIC Record Exists
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No
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Distribution Change Authority Correspondence
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None
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Abstract
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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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Report Availability
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Full text available
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Date Issued
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1965-05
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Provenance
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AFRL/VACA
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Type
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report
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Format
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1 online resource
FDLTDR64-152part02.pdf