High-speed tunnel tests of a 5 per cent. Chord dive-recovery flap on a NACA 0015 aerofoil

Abstract

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 10power6. All 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. The 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.