Analysis of the three-dimensional compressible turbulent boundary layer on a sharp cone at incidence in supersonic and hypersonic flow /
John C. Adams, Jr.

Description

Main Author

Adams, John C.

Related Names

ARO, Inc.
Arnold Engineering Development Center
United States. Air Force.

Language(s)

English

Published

Arnold Air Force Base, Tennessee : Von Kármán Gas Dynamics Facility, Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972.

Subjects

Boundary layer.
Aerodynamics, Supersonic.
Aerodynamics, Hypersonic.
Aérodynamique hypersonique.
Aérodynamique supersonique.
Couche limite.
Aerodynamics, Hypersonic.
Aerodynamics, Supersonic.
Turbulent boundary layer.
Space vehicles > Space vehicles / Atmospheric entry.

Summary

An analytical approach toward numerical calculation of the three-dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three-dimensional turbulent boundary-layer equations in conjunction with a three-dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.

Note

Report was prepared by ARO, Inc., a subsidiary of Sverdrup & Parcel and Associates, Inc.
"Final Report : July 1971 to February 1972."
"June 1972"--Cover

Physical Description

x, 82 pages : illustrations ; 27 cm

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