Hypersonic flow with combined leading-edge bluntness and boundary-layer displacement effect.

"This report is based on research sponsored by the U. S. Navy through the Office of Naval Research, Contract Nonr-2653(00)."

Evaluation of porous materials for boundary-layer control

ASTIA document no. AD 110582.

Lecture series "Boundary layer theory." /

Mode of access: Internet.

Stability of the boundary layer;

Reproduced from typewritten copy.

Catalytic surface recombination in boundary-layer profiles of the Falkner-Skan type.

"AFOSR 2071."

Pressure gradient effects on supersonic boundary layer turbulence : final report /

"Carried out by the Fluid Mechanics Section of the Aeronutronic Division of the Ford Aerospace & Communications Corporation."

Boundary layer and wake modifications to compressor design systems : the effect of blade-to-blade flow variations on the mean flow field of a transonic rotor : final report, 01 September 1976-31 August 1978 /

"AFAPL-TR-79-2010."

Helium injection into the boundary layer at an axisymmetric stagnation point

"Contract no. AF 33(616)-7661, Project no. 7064, Task no. 70169."

On the inviscid stability of the boundary layer on a flexible wall,

"This report is based on research sponsored by the U.S. Navy through the Office of Naval Research, Contract Nonr-2653(00)"

M=3 turbulent boundary layer measurements at very high Reynolds numbers /

"Interim report for period January 1975 to September 1976."

The three-dimensional boundary layer /

Unclassified.

Eddy formation and the boundary layer in fish locomotion

Cover title.

Investigation of small surface protuberances upstream of turbulent boundary layer separation produced by a skewed shock wave at Mach 3 /

"Interim report for period January 1976-February 1976."

Shock tube test time limitation due to turbulent wall boundary layer.

At head of title: SSD-TDR-63-78. Report no. TDR-169 (3230-12)TR-3.

Control of hypersonic turbulent skin friction by boundary-layer combustion of hydrogen

Shvab-Zeldovich coupling of flow variables has been used to extend Van Driest's theory of turbulent boundary-layer skin friction to include injection and combustion of hydrogen in the boundary layer. The resulting theory is used to make predictions of skin friction and heat transfer that are found to be consistent with experimental and numerical results. Using the theory to extrapolate to larger downstream distances at the same experimental conditions, it is found that the reduction in skin-friction drag with hydrogen mixing and combustion is three times that with mixing alone. In application to flow on a flat plate at mainstream velocities of 2, 4, and 6 knits, and Reynolds numbers from 3 X 10(6) to 1 x 10(8), injection and combustion of hydrogen yielded values of skin-friction drag that were less than one-half of the no-injection skin-friction drag, together with a net reduction in heat transfer when the combustion heat release in air was less than the stagnation enthalpy. The mass efficiency of hydrogen injection, as measured by effective specific impulse values, was approximately 2000 s.