Vortex Induced Rolling Moment on Cruciform Configured Missiles.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1974
- Accession Number
- AD0920266
Entities
People
- J. E. Milton
- R. W. Conlan
Organizations
- University of Florida