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Numerical computations of supersonic flow over a square cross-section missile

Author: Sidra I Silton; Jabaraj Sahu; U.S. Army Research Laboratory.
Publisher: Aberdeen Proving Ground, Md. : Army Research Laboratory, [2005]
Series: ARL-TR (Aberdeen Proving Ground, Md.), 3562.
Edition/Format:   eBook : Document : National government publication : English
Summary:
This report describes a computational study undertaken to determine the aerodynamics of a nonaxisymmetric missile with a square cross section. Numerical solutions have been obtained at supersonic speeds for various roll orientations and angles of attack using a two-equation Reynolds-averaged Navier-Stokes turbulence model. Numerical results show the qualitative features (vortices and cross-flow separation regions)  Read more...
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Material Type: Document, Government publication, National government publication, Internet resource
Document Type: Internet Resource, Computer File
All Authors / Contributors: Sidra I Silton; Jabaraj Sahu; U.S. Army Research Laboratory.
OCLC Number: 74280800
Notes: Title from PDF title screen (viewed on Nov. 2, 2010).
"August 2005."
Description: 1 online resource (viii, 42 pages) : illustrations (chiefly color).
Series Title: ARL-TR (Aberdeen Proving Ground, Md.), 3562.
Responsibility: Sidra I. Silton and Jubaraj Sahu.

Abstract:

This report describes a computational study undertaken to determine the aerodynamics of a nonaxisymmetric missile with a square cross section. Numerical solutions have been obtained at supersonic speeds for various roll orientations and angles of attack using a two-equation Reynolds-averaged Navier-Stokes turbulence model. Numerical results show the qualitative features (vortices and cross-flow separation regions) of the flow field at various stream wise positions along the missile configurations. Aerodynamic coefficients have been obtained from the computed solutions and found to match well with the available experimental data for these configurations. These numerical results show the ability of computational fluid dynamics techniques to accurately predict the aerodynamics of nonaxisymmetric missiles with a square cross section.

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Primary Entity

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