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 : JAN 1974

Pagination or Media Count : 39

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