INVESTIGATION OF NACA 65, (112) A111 (APPROX.) AIRFOIL WITH 0.35-CHORD SLOTTED FLAP AT REYNOLDS NUMBERS UP TO 25 MILLION

摘要

An investigation has been made in the Langley two-dimensional low—turtnilence tunnel and the Langley two-dimensional low—turbulence pressure tunnel to determine the highest maximum lift configurations (ideal configurations) of a 0.35-chord Blotted flap on an MACA 65(112)All (approx.) airfoil section. The scale effects on the aerodynamic characteristics were determined for Reynolds numbers ranging from 2.4 X 106 to approximately 25.0 x 106.