Investigation of Hypersonic Inlet Shock-Wave Boundary Layer Interaction: Part II - Continuous Flow Test and Analyses

Item

Title
Investigation of Hypersonic Inlet Shock-Wave Boundary Layer Interaction: Part II - Continuous Flow Test and Analyses
Date
1965
Index Abstract
Coming Soon
Photo Quality
Complete
Report Number
AFFDL TR 65-36
Corporate Author
General Electric Company
Laboratory
Air Force Flight Dynamics Laboratory
Extent
272
NTRL Accession Number
AD636981
Identifier
AD0636981
Access Rights
Distribution of this document is unlimited
Distribution Classification
1
Contract
AF 33(657)-11747
DoD Project
651-E
DoD Task
None Given
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Special Scanning Requirements
fold out pages
Abstract
The computational procedure developed in Phase I for estimating laminar boundary layer properties through impinging shock induced laminar boundary layer interactions was modified to account for entropy change of the inviscid streamlines in that isentropic assumptions were used in the initial formulation. Perturbation studies on the effects of wall shear on interaction length have identified the importance of the profile shape factor in such calculations. A Users' Manual for the laminar computational program is contained. Three incident shock models were designed for use in the experimental program conducted in the Ames 3.5 Foot Hypersonic Tunnel. Aided by analysis of the experimental data, a simplified flow model was formulated for the case of a two-dimensional turbulent boundary layer incident shock interaction.
Report Availability
Full text available
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Creator
Brown, David L.
Hoelmer, Werner
Kutschenreuter, Paul H., Jr.