Computational Study of High Supersonic Flow Over Boattails with Centered Propulsive Jets
Abstract
The present study concerns the ability to achieve good accuracy in missile after body flow predictions based on the Reynolds-averaged Navier-Stokes equations. The problems of numerical accuracy and turbulence modeling are addressed. By employing grids which were cell clustered and which have grid lines aligned with streamlines in shear layers, it was possible to obtain numerically accurate solutions and to obtain solutions at very high nozzle pressure ratios. The effects on turbulence of high Mach numbers and streamline curvature were examined. It was demonstrated that these phenomena have a significant effect on the turbulence and on the global flow characteristics such as base drag. Changes in base drag on the order of +/-20% for some afterbody flows can be attributed to Mach number and curvature effects. A modified form of the k-epsilon turbulence model which gives good accuracy for flows involving high Mach number and streamline curvature is presented. Keywords: Base drag, Turbulence modeling, Computational fluid dynamics, Truncation error estimates.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 31, 1989
- Accession Number
- ADA206364
Entities
People
- Robert E. Childs
Organizations
- Nielsen Engineering & Research (United States)