
Accession Number : ADA304471
Title : Numerical Investigation of Supersonic Base Flow with Base Bleed.
Descriptive Note : Final rept. Sep 94Oct 95,
Corporate Author : ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
Personal Author(s) : Sahu, Jubaraj ; Heavey, Karen R.
PDF Url : ADA304471
Report Date : DEC 1995
Pagination or Media Count : 40
Abstract : A zonal, implicit, timemarching NavierStokes computational technique has been used to compute the turbulent supersonic base flow over a cylindrical afterbody with base bleed. A critical element of calculating such flows is the turbulence model. Two eddy viscosity turbulence models have been used in the base region flow computations. These models include an algebraic turbulence model and a twoequation ke model. The ke equations are solved using an implicit algorithm, and calculations with the ke model are extended up to the wall. Flow field computations have been performed for a cylindrical afterbody at M approx. = 2.46 and at an angle of attack of a = 0. The results are compared to the experimental data for the same conditions and the same configuration. Details of the mean flow field as well as the turbulence quantities have been presented. In addition, the computed base pressure distribution has been compared with the experiment. In general, the ke turbulence model performs better in the near wake than the algebraic model and predicts the base pressure much better.
Descriptors : *TURBULENT FLOW, *SUPERSONIC FLOW, *BASE FLOW, MATHEMATICAL MODELS, ALGORITHMS, TIME DEPENDENCE, TURBULENCE, EDDIES(FLUID MECHANICS), COMPUTATIONAL FLUID DYNAMICS, ANGLE OF ATTACK, FINITE DIFFERENCE THEORY, FLOW FIELDS, CYLINDRICAL BODIES, SHEAR STRESSES, WAKE, AERODYNAMIC DRAG, MACH NUMBER, NAVIER STOKES EQUATIONS, VISCOSITY, PRESSURE DISTRIBUTION, BASE PRESSURE, DRAG REDUCTION, AFTERBODIES, BLEED SYSTEMS.
Subject Categories : Aerodynamics
Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE