Accession Number:

ADA184171

Title:

Three Dimensional Base Flow Calculation for a Projectile at Transonic Velocity

Descriptive Note:

Memorandum rept.

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s):

Report Date:

1987-06-01

Pagination or Media Count:

39.0

Abstract:

As part of an ongoing research program to develop predictive capabilities for projectile aerodynamics at transonic speeds, a three dimensional base flow code has been developed to compute the base region or wake flow behind the projectile. The time-marching, thin-layer, Navier-Stokes computational technique has been used, in conjunction with a unique flow field segmentation procedure, to compute the full flow field over a projectile including the base region at angle of attack. A flow field solution has been obtained for a typical artillery projectile at Mach number, M .96 and 4 deg angle of attack. Details of the flow field on the boattailed afterbody and in the base region are presented. Surface pressure, base pressure and aerodynamic coefficients are computed and compared with experiment.

Subject Categories:

  • Ballistics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE