AERODYNAMIC LOADS AT MACH NUMBERS FROM 0.70 TO 2.22 ON AN AIRPLANE MODEL HAVING A WING AND CANARD OF TRIANGULAR PLAN FORM AND EITHER SINGLE OR TWIN VERTICAL TAILS

Results of an investigation of the aerodynamic loads on a canard airplane model are presented without detailed analysis for the Mach number range of 0.70 to 2.22. The model consisted of a triangular wing and canard of aspect ratio 2 mounted on a Sears-Haack body of fineness ratio 12.5 and either a single body-mounted vertical tail or twin wing-mounted vertical tails of low aspect ratio and sweptback plan form. The body, right wing panel, single vertical tail, and left twin vertical tail were instrumented for measuring pressures. Data were obtained for angles of attack ranging from -4 degrees to +16 degrees, nominal canard deflection angles of 0 degrees and 10 degrees, and angles of sideslip of 0 degrees and 5.3 degrees. The Reynolds number was 2.9 x 10 to the 6th power based on the wing mean aerodynamic chord. (Author)