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Hypersonic Dynamic Stability: Part III. Unsteady Flow Field Program

Report Number: FDL TDR 64-149 Part 3
Author: Rie, H.
Author: Linkiewicz, E. A.
Author: Bosworth, F. D.
Corporate Author: General Electric Company
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1967-01
Pages: 311
Contract: AF 33(657)-11411
Project: 8219
Task: 821902
AD Number: AD0650879

Abstract:
A method of computing static and dynamic force and moment coefficients was prepared. The method provides for a complete inviscid flow field solution to be computed on the IBM 7094 machine. The solution provides values of all pertinent flow field parameters at a large number of points in the shock layer surrounding a pointed or spherically blunted body of revolution (or the analogous two-dimensional shapes) in supersonic or hypersonic flight. Perturbations (of each flow field parameter) due to angle of attack, rate of change of angle of attack, and pitch velocity are also computed. The force and moment coefficients are obtained by integrating the appropriate perturbations in pressure over the body surface. The above flow field capabilities were delivered in the form of magnetic tapes. A sample solution was demonstrated on the Wright-Patterson AFB computer installation on June 30-July 1, 1964. The analysis and programming of this solution is described.


Provenance:
Lockheed Martin Missiles & Fire Control
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