Accession Number:

ADA159017

Title:

Computational Simulation of Transonic Flow Over Projectile Rotating Band and Comparison with Experiment

Descriptive Note:

Memorandum rept.

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Report Date:

1985-05-01

Pagination or Media Count:

43.0

Abstract:

An azimuthal-invarient Navier-Stokes computational method is used to predict the transonic M 0.94 flow field about an artillery shell with and without a simulated rotating band. The pressure distribution calculations at zero angle of attack are compared to wind tunnel data and reasonable agreement is obtained. Pressures on the boattail afterbody are slightly reduced when a rotating band is added. The computational results show this to be due to local flow separation. The projectile drag coefficient is predicted to increase by 9 percent because of the rotating band for the conditions considered in the calculation. Keywords Pressure distribution data.

Subject Categories:

  • Numerical Mathematics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE