Roll Effects on Carryover for Hypersonic Delta Fin Missile

摘要

An Euler code is used to predict hypersonic missile flow fields and to determine the carryover factors for the effect of the body on wing lift K_W(B)and for the effect of the wing on body lift K_B(W). Results are presented for Mach 4,6, 8, and 10 at an angle of attack of 2 deg. The missile has a conical nose, a cylindrical fuselage with a 1-deg flare angle, and delta fins. Both × and + fin configurations are considered. Results are given for 20-and 30-deg semi vortex angles as a function of finspan to body radius(at fin leading edge), S/R_LE.