Unsteady Aerodynamics for Advanced Configurations: Part V - Unsteady Potential Flow Around Slender Bodies at Angles of Attack

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Report Number: FDL TDR 64-152 Part 5
Author(s): Li, T. C.
Corporate Author(s): North American Aviation, Incorporated
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1965-05
Pages: 52
Contract: AF 33(657)-10399
DoD Project: 1370
DoD Task: 137003
Identifier: AD0619397

In the portion of the study covered in this report, linearized theory is developed for potential flow around a slender body at not too large angles of attack. The solution is obtained by 'definitizing' the flow equation and rigorously satisfying the boundary conditions. This approach is completely different from conventional methods in that it constitutes a process of obtaining an analytic solution to the problem of potential flow by a 'march from the body' toward infinity. The extension of this new theory to the nonlinear case is immediate. Having shown it is possible to not restrict the Mach number, it is expected that the new theory should be applicable to the cases of subsonic, transonic and supersonic speeds as well.

Provenance: AFRL/VACA

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