誘導ローリング・モーメントの推定

抄録

The Semi-empirical formula of estimating the induced rolling moment has been developed. This formula is based on the concept that the magnitude of induced rolling moment is ruled by the dimension and structure of vortex wake behind missile, and is represented as a function of the parameter describing the relative dimension of vortex wake to the fin span. Since the formula includes a few assumptions and experimental parameters, agreement between the theory and experiment is not always good. However, the formula is useful to get qualitative understanding of the effect of induced rolling moment on missile, and moreover will give correct quantitative results if employed under accurate underStanding of the flow field around missile.
Presented in this paper are application of the formula to cruciform missile, comparisons between the flight data of sounding rockets and the simulation results obtained by this formula, and finally the effect of fin design on induced rolling moment.