The Air Force Armament Laboratory (AFATL) and the Arnold Engineering Development Center (AEDC) are participating in a joint effort to develop a trajectory control test vehicle (TCTV). The vehicle is to be used as a test bed for various seeker, autopilot, and flap actuator systems now in development. The aerodynamic characteristics of the vehicle were obtained from wind tunnel tests using a 0.25-scale model and are presented for Mach numbers 0.5 to 1.05 at angles of attack to 20 deg. The control effectiveness parameters presented were obtained using a single flap test technique in the wind tunnel. Also the computer-generated flight performance is presented for a nominal launch condition. (Author)


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