Title

An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers

Date

1965

Index Abstract

Coming Soon

Photo Quality

Complete

Report Number

AFFDL TR 65-123 Volume 1

Corporate Author

Lockheed-California Company

Laboratory

Air Force Flight Dynamics Laboratory

Extent

110

NTRL Accession Number

AD621343

Identifier

AD0621343

AD0621343

Access Rights

Notice(s)

Distribution Classification

1

Contract

AF 33(657)-8833

DoD Project

1366

DoD Task

136605

DTIC Record Exists

No

Distribution Change Authority Correspondence

None

Special Scanning Requirements

fold out pages

Abstract

Detailed boundary layer surveys were made on four axisymmetric compression surface models simulating typical hypersonic inlet compression surfaces at free stream Mach numbers ranging from 4 to 8. The four models were designed to provide isentropic compression at design Mach numbers of 5, 6, 8 and 10. The Mach 8 design model had provisions for wall cooling. Quantitative heat transfer measurements were made on the Mach 8 model at free stream Mach numbers of 5, 6, and 8. Two existing turbulent boundary layer theories were modified to account for the various phenomena found to be of importance in hypersonic boundary layers. Theoretical results from these methods were correlated with the experimental data. A significant observation of the present program is the powerful favorable effect of centrifugal force phenomena on boundary layer development in continuous adverse pressure gradients. It was found that these effects become more pronounced with increasing Mach number and reductions in free stream Reynolds number.

Report Availability

Full text available

Date Issued

1965-08

Provenance

Lockheed Martin Missiles & Fire Control

Type

report

Format

1 online resource

Subject

Carburetor Air Scoops

Turbulent Boundary Layer

Hypersonic Characteristics

Centrifugal Fields

Model Tests

Cooling

Wind Tunnel Models

Compressible Flow

Surfaces

Heat Transfer

Creator

Stroud, J. F.

Miller, L. D.