On the Normal Force and the Rolling Moment Due to Wing-Tail Interference of a Sounding Rocket Model

The induced normal force and rolling moment due to wing-tail interference is studied experimentally. Wind tunnel tests of TT-500A rocket model and a roll-controllable rocket model was performed at NAL 2m×2m Transonic Wind Tunnel and 1m×1m Blowdown Supersonic Wind Tunnel. Characteristics of normal-force-induced normal force and rolling moment, and rolling-moment-induced rolling moment on the tail-fins are obtained varying flow Mach number, angle of attack and bank angle. The results are compared with theoretical results based on the strip-theory.