Accession Number:

AD0920266

Title:

Vortex Induced Rolling Moment on Cruciform Configured Missiles.

Personal Author(s):

Corporate Author:

FLORIDA UNIV EGLIN AFB GRADUATE ENGINEERING CENTER

Report Date:

1974-01-01

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.

Descriptive Note:

Final rept. Sep 72-Nov 73,

Pages:

0039

Subject Categories:

Communities Of Interest:

Contract Number:

F08635-73-C-0009

File Size:

0.00MB

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