Elements of aerodynamics of supersonic flows.

Bibliography: p. 385-387.

Supersonic inlet diffusers and introduction to internal aerodynamics.

Includes bibliography.

Handbook of supersonic aerodynamics.

Includes bibliographies.

Material presented at the NACA Conference on Supersonic Aerodynamics at Ames Aeronautical Laboratory on June 4, 1946, National Advisory Committee for Aeronautics.

Includes bibliography.

Supersonic aerodynamics and rocket propulsion,

Includes bibliographical references.

Supersonic aeroelastic effects on static stability and control. Flight Control Laboratory. Contract nos. AF33 (616)-3577 and AF33(616)-6067. ARDC Project no. 8219. Task no. 82158.

pt. 3. Aeroelastic interaction, by V. W. Donato.

The calculation of three-dimensional supersonic flows around spherically-capped smooth bodies and wings

"Work performed for the Air Force Flight Dynamics Laboratory...by the Aerodynamics Research Department of the Northrup Corporation, Aircraft Division."

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."

Reduction of drag due to lift at supersonic speeds

"Aeronautical Research Laboratory, Contract no. AF 33(616)-2170, Project no. 1366."

Linearized theory of conical supersonic flow with application to triangular wings /

Loose-leaf.

Quasi-three-dimensional supersonic viscid/inviscid interactions including separation effects : final report for period, 1 October 1972- 30 September 1975 /

Bibliography: p. 77-83.

Pressure distribution on a body a revolution in supersonic flight, by Robert R. Reynolds.

"This report appears as an appendix to the National Applied Mathematics Laboratories Quarterly report of projects and publications, January through March 1952."

Reverse flow and supersonic interference.

"AFOSR TN-58-625. ASTIA doc. no. AD 162 155."

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.