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."

Effect of thermal stresses on the aeroelastic stability of supersonic wings.

Mode of access: Internet.

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.

The flow of a supersonic jet from a vessel with plane walls. Iztecheniye sverhzvookovoy strooi iz sosooda s ploskimi stenkami.

Translation of Istechenie sverkhzvukovoĭ strui iz sosuda s ploskimi stenkami (romanized form)

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.

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

Bibliography: p. 77-83.

Uniformly valid second-order solution for supersonic flow over cruciform surfaces,

"CM-1019."

Heat Transfer Measurements in a Supersonic Film Flow

This thesis presents measurements of wall heat flux and flow structure in a canonical film cooling configuration with Mach 2.3 core flow in which the coolant is injected parallel to the wall through a two-dimensional louver. Four operating conditions are investigated: no film (i.e. flow over a rearward-facing step), subsonic film, pressure-matched film, and supersonic film. The overall objective is to provide a set of experimental data with well characterized boundary conditions that can be used for code validation. The results are compared to RANS and LES simulations which overpredict heat transfer in the subsonic film cases and underpredict heat transfer in supersonic cases after film breakdown. The thesis also describes a number of improvements that were made to the experimental facility including new Schlieren optics, a better film heater, more data at more locations, and a verification of the heat flux measurement hardware and data reduction methods.

Uniform second-order solution for supersonic flow over delta wing using reverse-flow integral method,

"CM-1034."

Reverse-flow integral methods for second-order supersonic flow theory,

"CM-1033."

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."