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):

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.

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE