Accession Number : ADP001931

Title :   Computation of Flow Past a Hypersonic Cruiser,

Corporate Author : AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH

Personal Author(s) : Shang,J. S. ; Hankey,W. L.

Report Date : 1983

Pagination or Media Count : 9

Abstract : Numerical simulations of a hypersonic cruiser were accomplished by means of the mass-averaged Navier-Stokes equations at a nominal Mach number of six and a Reynolds number of fifteen million. The computations of flow at the zero and ten degree angles of attack were performed on a CRAY-1 computer utilizing a grid consisting of over 56,000 points. The present results adopting a branch-cut mesh system yielded superior numerical resolution over the previous solution using a wrap-around grid distribution. Numerical results are presented showing the detailed flow field structure, density and vorticity distribution, and velocity field. These results indicate that the wing-fuselage configurations investigated generates an unfavorable interference factor. (Author)

Descriptors :   *Flow fields, Hypersonic flow, Hypersonic vehicles, Wing body configurations, Navier Stokes equations, Computerized simulation, Computations, Mach number, Reynolds number

Distribution Statement : APPROVED FOR PUBLIC RELEASE