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Analysis of Three-dimensional Inviscid Supersonic Flow Between a Body and an Outer Wall

Author: W. C. Armstrong

Publisher:

Published: 1976

Total Pages: 98

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The three-dimensional inviscid supersonic flow equations are solved for the flow over a body located within a duct. Numerical solutions are obtained by use of the reference plane method of characteristics technique. Results of the analysis are compared with experimental test body pressure distributions obtained with an off-design jet stretcher system. The analysis is sufficiently general so that a variety of internal flows may be predicted. A computer program listing and an example problem are presented.

Scientific and Technical Aerospace Reports

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Publisher:

Published: 1994

Total Pages: 372

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Aeronautical Engineering

Author:

Publisher:

Published: 1971

Total Pages: 580

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A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)

A Method of Characteristics Computer Program for Three-dimensional Supersonic Internal Flows

Author: W. C. Armstrong

Publisher:

Published: 1979

Total Pages: 98

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The reference-plane method of characteristics is applied to the computation of the supersonic flow in a three-dimensional (3-D) channel such as a propulsion nozzle. The fluid is assumed to be an inviscid ideal gas and the flow is assumed to be shock-free, although it can be rotational. Both the basic equations and the numerical procedures are described, as is the computer program, which was written in FORTRAN IV language for the IBM 370/165 computer. The validity of the computer program was established by computing, in various ways, an axisymmetric nozzle flow as a three-dimensional flow; the numerical results are in good agreement with the results from a well-established computer program for axisymmetric flow. (Author).

Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack

Author: G. Moretti

Publisher:

Published: 1968

Total Pages: 36

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Comparisons are made between the cylindrical and polar coordinate system used in determining the three-dimensional shock layer flow over the nose region of a blunted supersonic vehicle. Jusfification for the development of a polar coordinate system is given and an outline for such development is presented. Results from the polar coordinate system are given as is the limiting useful range.

Government Reports Annual Index: Keyword A-L

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Publisher:

Published: 1976

Total Pages: 1052

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Analysis of the Three-dimensional Compressible Turbulent Boundary Layer on a Sharp Cone at Incidence in Supersonic and Hypersonic Flow

Author: John C. Adams

Publisher:

Published: 1972

Total Pages: 98

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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.