Simulation of Three-Dimensional Shear Flow Around a Nozzle-Afterbody at High Speeds

[+] Author and Article Information
Oktay Baysal

Old Dominion University, Norfolk, VA 23529

Wendy B. Hoffman

Mechanical Engineering and Mechanics Department, Old Dominion University, Norfolk, VA 23529

J. Fluids Eng 114(2), 178-185 (Jun 01, 1992) (8 pages) doi:10.1115/1.2910013 History: Received March 04, 1991; Online May 23, 2008


Turbulent shear flows at supersonic and hypersonic speeds around a nozzle-afterbody are simulated. The three-dimensional, Reynolds-averaged Navier-Stokes equations are solved by a finite-volume and implicit method. The convective and the pressure terms are differenced by an upwind-biased algorithm. The effect of turbulence is incorporated by a modified Baldwin-Lomax eddy viscosity model. The success of the standard Baldwin-Lomax model for this flow type is shown by comparing it to a laminar case. These modifications made to the model are also shown to improve flow prediction when compared to the standard Baldwin-Lomax model. These modifications to the model reflect the effects of high compressibility, multiple walls, vortices near walls, and turbulent memory effects in the shear layer. This numerically simulated complex flowfield includes a supersonic duct flow, a hypersonic flow over an external double corner, a flow through a non-axisymmetric, internal-external nozzle, and a three-dimensional shear layer. The specific application is for the flow around the nozzle-afterbody of a generic hypersonic vehicle powered by a scramjet engine. The computed pressure distributions compared favorably with the experimentally obtained surface and off-surface flow surveys.

Copyright © 1992 by The American Society of Mechanical Engineers
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