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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
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.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE