Abstract:
The static-pressure distribution on the surface of a thin delta wing of aspect ratio 1.616 was measured at several incidences in subsonic flow, and the results were analysed to investigate the development with incidence of the leading-edge vortices above the wing and of the chordwise distribution of the aerodynamic loading on it. The results were compared with those obtained from ealier tests to demonstrate how the chordwise distribution of aerodynamic loading on a slender wing is affected by its aspect ratio, thickness and wing-tip shape.
