Accession Number : AD0650879

Title :   HYPERSONIC DYNAMIC STABILITY. PART III. UNSTEADY FLOW FIELD PROGRAM.

Descriptive Note : Final rept., May 63-Jun 64

Corporate Author : GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV

Personal Author(s) : Rie,H. ; Linkiewicz,E. A. ; Bosworth,F. D.

Report Date : JAN 1967

Pagination or Media Count : 306

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. (Author)

Descriptors :   (*REENTRY VEHICLES, STABILITY), (*HYPERSONIC FLIGHT, REENTRY VEHICLES), (*FLOW FIELDS, ATMOSPHERE ENTRY), COMPUTER PROGRAMS, DYNAMICS, BOUNDARY LAYER, BODIES OF REVOLUTION, SUPERSONIC FLIGHT, PERTURBATION THEORY, ANGLE OF ATTACK, PITCH(MOTION), COMPUTER PROGRAMMING

Subject Categories : Unmanned Spacecraft
      Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE