High-Speed Tunnel Tests of a 5 per cent. Chord Dive-Recovery Flap on a NACA0015 Aerofoil

摘要

Pressure plotting tests were made in the Royal Aircraft Establishment High Speed Tunnel on a parallel wooden NACA 0015 wing with dive-recovery flap. The Mach number was varied between 0-30 and 0-80, and the Reynolds number was kept constant at 1 -4 x 106.nAll combinations of the following were tested :—flap position 0-2c, 0-3c, 0-4c;flap angle 20 deg, 40 deg, incidence 0 deg, 4 deg. The flap-chord/wing-chord ratio was 0.05.nThe report presents a general picture of the action of a dive-recovery flap on a wing. The data are, however, too limited to permit the formulation of general design recommendations.