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An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers.

AD621343

Publication Date	1965
Personal Author	Stroud, J. F.; Miller, L. D.
Page Count	2
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.
Keywords	Air scoops Turbulent boundary layer Hypersonic characteristics Centrifugal fields Model tests Cooling Wind tunnel models Compressible flow Surfaces Heat transfer
Corporate Authors	Lockheed-California C Burbank
Document Type	Technical Report
Title Note	Final rept., vol. 1, Jun 62-Nov 64.
NTIS Issue Number	196521
Contract Number	AF33 657 8833

An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers.

An Experimental and Analytical Investigation of Hypersonic Inlet Boundary Layers.
AD621343

Publication Date	1965
Personal Author	Stroud, J. F.; Miller, L. D.
Page Count	2
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.
Keywords	Air scoops Turbulent boundary layer Hypersonic characteristics Centrifugal fields Model tests Cooling Wind tunnel models Compressible flow Surfaces Heat transfer
Corporate Authors	Lockheed-California C Burbank
Document Type	Technical Report
Title Note	Final rept., vol. 1, Jun 62-Nov 64.
NTIS Issue Number	196521
Contract Number	AF33 657 8833