Transonic Navier-Stokes Computations for a Projectile at Angle of Attack and Comparison with Experiment
Abstract
The objective of this work is to investigate the ability of the Pulliam and Steger implicit Navier-Stokes code to predict the transonic, viscous flow about a body of revolution at small angles of attack. The computations have been performed for the geometry and test conditions of wind tunnel experiments. This includes surface pressure distributions and boundary layer surveys at Mach numbers of 0.94 and 0.97 and at 0 and 4 degrees angle of attack. Particular attention is focused on the boattail afterbody region because of the strong shock wave-boundary layer interactions and near wake influences which occur there. The results show good quantitative agreement between prediction and experiment for both pressure distribution and boundary layer profiles at zero angle of attack. To accurately predict the boattail characteristics in the final 2-3 percent of the body length, it was found necessary to correctly model the base and near wake flow. At four degrees angle of attack, the agreement is only fair.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1988
- Accession Number
- ADA202411
Entities
People
- Ching-chang Chieng
- James E. Danberg
Organizations
- Ballistic Research Laboratory