Accession Number:

AD0679755

Title:

VORTEX INDUCED ROLLING MOMENTS ON FINNED MISSILES AT HIGH ANGLE OF ATTACK

Descriptive Note:

Corporate Author:

BOSTON UNIV MA ENGINEERING LABS

Personal Author(s):

• Udelson, Daniel G.

Report Date:

1968-11-01

Pagination or Media Count:

54.0

Abstract:

Previous analytical studies endeavoring to account for vortex induced rolling moments on missiles have not successfully correlated with experimental results. This points up the need for a theoretically more sophisticated treatment, which the present work attempts to satisfy. A model for the two dimensional cross flow past the tail body combination is employed and the Blasius complex contour integral used to find the moments. The final result contained herein presents the complete mathematical solution for the two dimensional ideal flow past a planar tail body combination. It is in closed analytic form with the exception of one definite integral which has been reduced to a form suitable for numerical calculation. All terms of the solution integrated as well as the integral are best calculated for various values of the parameters on a large scale digital computer.

Descriptors:

• *FIN STABILIZED AMMUNITION
• MAGNUS EFFECT
• YAW
• MOMENTS
• VORTICES
• ANGLE OF ATTACK
• TWO DIMENSIONAL FLOW
• NUMERICAL METHODS AND PROCEDURES
• INTEGRAL EQUATIONS
• ROCKETS
• FINS
• FORCE(MECHANICS)
• SPIN STABILIZATION
• ROCKET TRAJECTORIES
• MATHEMATICAL MODELS
• PITCH(MOTION)

Subject Categories:

• Ammunition and Explosives
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE