Title

Hypersonic Dynamic Stability: Part III. Unsteady Flow Field Program

Date

1967

Index Abstract

Coming Soon

Photo Quality

Not Needed

Report Number

FDL TDR 64-149 Part 3

Creator

Rie, H.

Linkiewicz, E. A.

Bosworth, F. D.

Corporate Author

General Electric Company

Laboratory

Air Force Flight Dynamics Laboratory

Extent

311

Identifier

AD0650879

Access Rights

Distribution of this document is unlimited

Distribution Classification

1

Contract

AF 33(657)-11411

DoD Project

8219

DoD Task

821902

DTIC Record Exists

No

Distribution Change Authority Correspondence

None

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.

Report Availability

Full text available

Date Issued

1967-01

Provenance

Lockheed Martin Missiles & Fire Control

Type

report

Format

1 online resource