Tests in the Ames 40- by 80-foot Wind Tunnel of an Airplane Model with an Aspect Ratio 4 Triangular Wing and an All-movable Horizontal Tail - High-lift Devices and Lateral Controls

Memorandum presenting tests of a triangular-wing-airplane model equipped with high-lift devices and lateral and directional controls. The model consisted of an aspect ratio 4 triangular wing in combination with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail. Results regarding the effects of flap deflection and tail incidence on the pitching moment characteristics, lift and drag characteristics, and rudder effects are provided.