Accession Number:

ADA171461

Title:

Supersonic Flow Over Cylindrical Afterbodies with Base Bleed.

Descriptive Note:

Final rept.,

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s):

• Sahu,Jubaraj

Report Date:

1986-06-01

Pagination or Media Count:

31.0

Abstract:

Computations of supersonic flow over two cylindrical afterbodies have been made using a thin-layer Navier-Stokes base flow code. The capability to compute the base flow with base bleed at supersonic speeds has been developed and used to show the effect of mass injection on the base pressure or base drag. Solutions have been obtained for a projectile and a missile configuration having cylindrical afterbodies. Numerical results show the effect of base bleed on the near wake flow field. The rise in base pressure or reduction in base drag has been clearly predicted for various mass injection rates and comparison with experimental data shows generally good agreement.

Descriptors:

• *PROJECTILES
• *AERODYNAMIC DRAG
• *SUPERSONIC FLOW
• *NAVIER STOKES EQUATIONS
• *BASE FLOW
• VELOCITY
• COMPUTATIONS
• CYLINDRICAL BODIES
• MACH NUMBER
• BASE PRESSURE

Subject Categories:

• Ammunition and Explosives
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE