
Accession Number : ADA111790
Title : Computation of ThreeDimensional Viscous Flow over Blunt Lifting Bodies at High Angle of Attack,
Corporate Author : VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG DEPT OF AEROSPACE AND OCEAN ENGINEERING
Personal Author(s) : Szema,K Y ; Lewis,C H
PDF Url : ADA111790
Report Date : 14 May 1981
Pagination or Media Count : 26
Abstract : The viscous shocklayer equations for threedimensional hypersonic flows of a perfect gas or equilibrium air over lifting bodies at high angles of attack have been developed. For the complex threedimensional reentry vehicle geometries of interest, the resulting equations are written in a nonorthogonal, bodyoriented coordinate system, and the three velocity components are defined in the nonorthogonal coordinate directions. Since the viscous shocklayer governing equations are parabolic in both the streamwise and crossflow directions, the equations are solved by a highly efficient finitedifference scheme. The principal advantages of this technique are the numerical method can be used to predict the flowfield about arbitrary geometries in both subsonic and supersonic regions, the solution is direct, and the effects of inviscidviscous interactions are uniformly valid throughout the shock layer. Numerical solutions have been obtained for a 1:1.4 (perfect gas), 1:2 ellipsoid in a perfect gas or equilibrium air and the nose portion of the shuttle orbiter at zero, 10 and 25deg angles of attack. Comparisons were made with inviscid solutions and existing experimental data, and the agreement is good for all the cases. (Author)
Descriptors : *Hypersonic flow, *Lifting bodies, Viscous flow, Three dimensional flow, Blunt bodies, Angle of attack, High angles, Finite difference theory, Navier Stokes equations, Shock, Layers, Reentry vehicles, Chemical equilibrium, Air, Flow fields, Mathematical prediction, Numerical analysis
Subject Categories : Guided Missile Reentry Vehicles
Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE