Kinetic study of the hypersonic flow past the leading edge of a flat plate.

Vita.

Wave superheater hypersonic tunnel; semiannual report,

"AEDC TDR-62-54. Program area 750A. AFSC project 4773. Contract no. AF40(600)-804."

The blunt-body problem in hypersonic flow at low Reynolds number.

"Contract no. Nonr 2653(00)"

Engineering design of a wave superheater facility for hypersonic research and development.

AFOSR-TN-59-108; AD-210224.

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)."

Hypersonic research summary.

"Contract AF 18(603)-141. Mechanics Division, Air Force Office of Scientific Research, Air Research and Development Command, Washington."

Low-density research in the hypersonic shock tunnel

"The experimental study reported here has been performed under the sponsorship of the Fluid Dynamics Branch, Aeronautical Research laboratories of the U.S. Air Force Air Research and Development Command, Contract no. AF 33(616)-6025."

Expansion of gas clouds and hypersonic jets bounded by a vacuum.

"SSD-TDR-62-96. Report no. TDR-169 (3230-12) TR-1. Contract no. AF 04(695)-169."

48-inch hypersonic shock tunnel; description and capabilities.

Mode of access: Internet.

Hypersonic dynamic stability.

pt. 1. Summary [by] L. A. Marshall.--pt. 2. Conical body experimental program [by] R. B. Hobbs, Jr.--pt. 3. Unsteady flow field program [by] H. Rie, E. A. Linkiewicz [and] F. D. Bosworth.

Hypersonic free flight research.

pt. 1 Instrumentation evaluation and data analysis, by R. W. Bogle and R. J. Magnus.--pt. 2 Investigations of heat trasfer and aerodynamic stability, by O. R. Burggraf.

Investigation of feasibility of utilizing available heat resistant materials for hypersonic leading edge applications.

"Volumes I through VIII are unclassified while volume IX is classified secret."

Hypersonic gas dynamic charts for equilibrium air /

Errata sheet inserted.

Skin friction, heat transfer, and pressure measurements on hypersonic inlet compression surfaces in the Mach number range 7.5 to 16.

Cornell Aeronautical Laboratory, Inc., Buffalo. Report no. AA-1948-Y-3

The shock layer concept and three-dimensional hypersonic boundary layers.

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