Book Description

Wind tunnel tests were conducted to determine the drag og two-dimensional wing sections operating in a near-vertical flow condition. Various leading-and trailing-edge configurations, including plain flaps of 25, 30, and 35% chord were tested at angles of attack from-75 to -105deg. Reynolds numbers examined ranged from approximately 0.6 to 1.4 million. The data were obtained using a wind tunnel force and moment balance system and arrays of chordwise pressure orifices. The results showed that significant reductions in drag, beyond what would be expected by virtue of the decreased frontal area, were obtainable with geometries that delayed flow separation. Rapid changes in drag with angle of attack were noted for many configurations. The results, however, were fairly insensitive to Reynolds number variations. Drag values computed from the pressure data generally agreed with the force data within 2%. Keywords: Download; Two-dimension wing; Leading edge; trailing edge; Wing flap; Wing slots; Wing slats; Wing spoiler.