Accession Number : ADA189212
Title : A Numerical Study of Flare Stabilized Projectiles at Mach 7.0.
Descriptive Note : Final rept. Jul 85-Jun 86,
Corporate Author : AIR FORCE ARMAMENT LAB EGLIN AFB FL
Personal Author(s) : Hughson, Montgomery C ; Chapman, Gary T
PDF Url : ADA189212
Report Date : Jan 1988
Pagination or Media Count : 11
Abstract : The effect of nose shape on two flare stabilized projectiles was studied using a Parabolized Navier-Stokes code. Pressure coefficients, forces and moments, skin friction coefficients, and Stanton number calculations are presented for the hemisphere-cylinder-flare and the cone-cylinder-flare configurations. Pitching moment and static margin plots versus flare angles and flare lengths are presented in a parametric study to show aerodynamic stability effects. Distinctly different flow field values of pressure, local Mach number, and dynamic pressure were generated by the two different nose configurations. These flow field values just upstream of the flare were examined. The code demonstrated its value as a design tool by making a clear distinction between aerodynamically stable characteristics for this variety of nose shapes, flare angles, and flare lengths.
Descriptors : *PROJECTILES, *FLARED AFTERBODIES, AERODYNAMIC FORCES, AERODYNAMIC STABILITY, AERODYNAMICS, COEFFICIENTS, DYNAMIC PRESSURE, FLOW FIELDS, MACH NUMBER, MOMENTS, NAVIER STOKES EQUATIONS, NOSES, NUMERICAL ANALYSIS, PARABOLAS, PITCH(MOTION), PLOTTING, PRESSURE, SHAPE, SKIN FRICTION, STABILITY, STATICS, PROJECTILE NOSES, MATHEMATICAL MODELS
Subject Categories : Ammunition and Explosives
Distribution Statement : APPROVED FOR PUBLIC RELEASE