Force and Pressure Measurements on a Research Model with a Low-, Mid-, and T-Tail at Mach Numbers of 0.60 to 0.90. Volume I. Summary Report

An investigation of the effects of a low-, mid-, and T-Tail on configuration aerodynamics was carried out in the NASA/Ames Research Center 14-Foot Transonic Wind Tunnel. A baseline wing and a wing refined with the use of numerical optimization were tested alone and in conjunction with a horizontal tail in a low-, mid-, and T-Tail arrangement. Wing and horizontal tail pressure data and force data were obtained in the Mach number range 0.60 to 0.90 and at angles of attack from -6 to +28 deg. The all-flying horizontal tail was tested at deflection angles of -10, 0, and +10 deg. The refined wing showed positive drag improvements over most of the Mach number range. The low-tail proved to be slightly more favorable than the T-Tail at low CL's. (Author) See also Volume 2, AD-A124 068.