Calculation of high speed inlet flows using the Navier-Stokes equations.
Volume II,
User's and programmer's guide /
Doyle D. Knight.
Description
- Language(s)
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English
- Published
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Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1980.
- Summary
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A set of computer programs has been developed to calculate the flowfield in two-dimensional mixed-compression high speed inlets. The full mean compressible Navier-Stokes equations are utilized, with turbulence represented by an algebraic eddy viscosity model which incorporates a relaxation correction. A curvilinear body-oriented coordinate system is employed to allow handling of arbitrary inlet contours. Boundary layer bleed is incorporated. The numerical algorithm of MacCormack is employed to solve the Navier-Stokes equations. A variety of techniques are incorporated to improve code efficiency, including time-splitting of the finite-difference operators, automatic mesh-splitting, and a separate algorithm for the treatment of the viscous sublayer portion of the turbulent boundary layers. The numerical codes have been successfully applied to the calculation of a variety of flows including shock-boundary layer interaction on a flat plate (including both unseparated and separated cases), and three different simulated high speed inlet configurations. In all cases, good agreement was obtained with the experimental data.
- Note
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"This report was prepared by the Department of Mechanical, Industrial and Aerospace Engineering, Rutgers University, New Brunswick, New Jersey."
"Final Report for period April 1978-September 1979."
"February 1980."
- Physical Description
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viii,129 pages :
illustrations, figures, tables ;
28 cm.
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