Title

Design Analysis Summary Of Two Force-Balance Hypersonic Inlet Configurations

Date

1964

Index Abstract

Coming Soon

Photo Quality

Complete

Report Number

FDL TDR 64-19

Creator

Kutschenreuter, Paul H., Jr.

Balent, Richard L.

Richy, George K.

Corporate Author

Air Force Flight Dynamics Lab Wright-Patterson AFB Ohio

Laboratory

Air Force Flight Dynamics Laboratory

Extent

48

Identifier

AD0437909

Access Rights

OTS

Distribution Classification

1

Contract

Laboratory Research - No Contract

DoD Project

1366

DoD Task

136605

DTIC Record Exists

No

Distribution Change Authority Correspondence

None

Abstract

Two hypersonic inlet models were designed for force balance testing in the Cornell Aeronautical Laboratory 48-inch shock tunnel over a Mach Number range of 8 to 16. The performance of these models is to be established experimentally on the basis of their measured internal drag. Reasons for considering this method of establishing hypersonic inlet performance and use of the associated drag equivalent pressure recovery are discussed. The design of these models, the resulting inlet geometry, and the related performance caluclations are described.

Report Availability

Full text available

Date Issued

1964-03

Provenance

Lockheed Martin Missiles & Fire Control

Type

report

Format

1 online resource