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This work is part of a cooperative research, development, test and evaluation program that brings scientists and engineers from various English-speaking countries together for collaborative studies to improve technology to solve technical problems. The current TTCP work project WTP-2 KTA 2-12, 'Application of CFD to the prediction of Missile Body Vortices' focuses on the ability of the three-dimensional Navier-Stokes equations to predict flowfields about high length-to-diameter bodies at moderate angles of attack (8 deg <a <14 deg) for supersonic Mach numbers. This report documents this author's computational results for the five test cases. The five test cases are as follows. Mach 1.45 at a = 14 deg, Mach 1.8 at a = 14 deg, Mach 2.5 at a = 14 deg, Mach 3.5 at a = 8 deg, and Mach 3.5 at a = 14 deg. The experimental body is 13 diameters long with the diameter of the cylindrical afterbody of 3.7 inches. Laminar and turbulent computations are shown with comparisons to experimental data. The experimental validation data was provided by the Defence Research Agency (UK). The computations were performed with an existing Navier-Stokes code FDL3DI developed in the Wright Laboratory. The sur

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Author

Josyula, Eswar,

Publisher

Flight Dynamics Directorate, Wright Laboratory, Air Force Materiel Command, United States Air Force, 1997.

Published

1997

Language

EN

Category

nonfiction