Title

The Effects of Active Cooling on the Aerodynamic and Aerothermodynamic Characteristics of Slender Bodies of Revolution

Date

1964

Index Abstract

Coming Soon

Photo Quality

Not Needed

Report Number

AFFDL TR 64-187

Creator

Leadon, B. M.

Rosciszeski, Jan.

Gallaher, W. H.

Holst, W. R.

Carter, W. V.

Corporate Author

General Dynamics/Convair

Laboratory

AF Flight Dynamics Laboratory

Extent

106

NTRL Accession Number

AD615471

Identifier

AD0615471

Access Rights

Notice(s)

Distribution Classification

1

Contract

AF 33(657)-11679

DoD Project

1366

DoD Task

136607

DTIC Record Exists

No

Distribution Change Authority Correspondence

None

Abstract

A new self consistent method has been developed for calculation of boundary layer with mass injection. The system of partial differential equations is reduced to a system of ordinary differential equations by integration over different strips. The velocity and enthalpy profiles are assumed to be expressed by series of error functions. A method of calculating the initial velocity and enthalpy profiles, based on an analysis of singularity, is presented herein. The calculation of the initial profiles is reduced to the solution of a system of transcendential equations. The initial derivatives are calculated from linearlized equations near the singular points and provide a smooth start of integration of the downstream equations. The present method was applied to the cases of a sharp edged body and a blunt body. In addition to the velocity and enthalpy profiles, the pressure distribution and shock layer thickness can be calculated from generalized Newtonian expressions developed as a part of this effort.

Report Availability

Full text available

Date Issued

1964-12

Provenance

Lockheed Martin Missiles & Fire Control

Type

report

Format

1 online resource