Accession Number:

AD0920266

Title:

Vortex Induced Rolling Moment on Cruciform Configured Missiles.

Descriptive Note:

Final rept. Sep 72-Nov 73,

Corporate Author:

FLORIDA UNIV EGLIN AFB GRADUATE ENGINEERING CENTER

Personal Author(s):

• Conlan, R. W.
• Milton, J. E.

Report Date:

1974-01-01

Pagination or Media Count:

39.0

Abstract:

A simplified treatment of vortex induced rolling moment on cruciform configured missiles is presented. Potential flow is assumed along with steady state conditions so that the problem can be classified as a pure boundary value problem. The final integral for roll moment is made analytic so that residue calculus can be used to find a closed form solution. Comparison of this equation with strip theory for a cruciform finned missile for various fin span-to-body radius ratios is good.

Descriptors:

• (*CRUCIFORM WINGS
• AERODYNAMIC CHARACTERISTICS)
• (*VORTICES
• GUIDED MISSILE TRAJECTORIES)
• COMPUTATIONS
• TORQUE
• ROLL
• MOMENTS
• AERODYNAMIC CONFIGURATIONS
• BOUNDARY VALUE PROBLEMS
• FLOW FIELDS
• STEADY STATE
• CALCULUS
• PRESSURE
• DISTRIBUTION
• MATHEMATICAL MODELS
• FINS
• COEFFICIENTS
• DEFLECTION
• ANGLE OF ATTACK
• COMPLEX VARIABLES

Subject Categories:

• Aircraft
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE