Investigation of the flow over simple bodies at Mach numbers of the order of 20 /

"It is shown that adequate means are available for calculating inviscid direct and induced pressures on simple axisymmetric bodies at zero angle of attack. The extent to which viscous effects can alter these predictions is indicated. It is also shown that inviscid induced pressures can significantly affect the stability of blunt, two-dimensional flat wings at low angles of attack. However, at high angles of attack, the inviscid induced pressure effects are negligible."

An investigation of the exact solutions of the linearized equations for the flow past conical bodies,

Reproduced from type-written copy.

NACA research memorandum.

Description based on: RM no. A6G24 (May 12, 1947); title from cover.

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 turbulent boundary layer with variable Prandtl number.

Mode of access: Internet.

An analytical and experimental study of the ionized flow field about a hemisphere cylinder and its effect on the radiation pattern of a slot antenna

Mode of access: Internet.

Airplane design; a textbook of airplane layout and stress analysis calculations with particular emphasis on economics of design.

"First three editions comprising 2400 copies were published between Dec. 1934 and June 1939."

Recirculation principle for ground effect machine two-dimensional tests.

"Task 9R99-01-005-04. Contract DA 44-177-TC-710."

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.

A study of finite-difference methods as applied to hypersonic viscous shock-layer equations

"Contract no. Nonr 2653(00)."

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."