  The occurrence of asymmetric rolling moments in wraparound fin (WAF)
projectiles, even at zero free stream angle of attack, and their potential to
induce roll reversal and resonant instabilities has long been recognized. The
induced rolling moment is seen to flip sign depending on the WAF configuration
(with concave surface leading into the roll or vice versa), and between
subsonic and supersonic Mach numbers. In this work, we propose a simple
mechanism that can explain the anomalous rolling behavior of WAF projectiles in
the subsonic regime. By modeling the curved fin by discrete span-wise linear
segments, the wraparound fin can be approximated as a wing with a deflected
winglet, and the experimental data available in the literature for such wing
configurations can be applied to the curved fin of WAF projectiles. The lifting
characteristic of the curved fin can be seen to differ depending on whether the
wingtip appears to be deflected up or down relative to the local flow incidence
angle. Based on this differential lift between a pair of oppositely-placed
curved fins on a WAF rocket, it becomes possible to explain the observed sign
of the induced rolling moment as well as its dependence on the free stream
angle of attack for small values of the angle of attack. The physical mechanism
for the differential lift, and hence the induced rolling moment, can be traced
to the span-wise location and the liftoff height of the tip vortex from the
wraparound fin tips.
