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

Item

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