A possible reason is suggested for the induced rolling moments occurring on wraparound-fin configurations in subsonic flight at zero angle of attack. The subsonic potential flow over the configuration at zero incidence is solved numerically. The body is simulated by a distribution of sources along its axis, and the fins are described by a vortex-lattice method. It is shown that rolling moments can be induced on the antisymmetric fins by the radial flow generated at the base of the configuration, either over the converging separated wake, or over the diverging plume of rocket motor.
The evaluation of the rolling moments induced by wraparound fins
1983-07-01
Conference paper
No indication
English
Aerodynamics of wraparound fins
NTRS | 1983
|Aerodynamics of wraparound fins
AIAA | 1983
|