An investigation has been made in the Langley 8-foot transonic pressure tunnel to determine the transonic chordwise pressure distri-bution of three paraglider models through an angle-of-attack range from 10° up to 90°. Three rigid metal models simulated a paraglider which had a basic flat planform with leading edges swept back 45°. These configurations had leading-edge sweep angles of 6l.6°, 52.5°, and 48.6°, which resulted in one-half-circle, one-third-circle, and one-quarter-circle curvature of the semispan trailing edges when viewed from downstream. The results of the investigation are presented as curves of chordwise pressure distributions at four spanwise locations for each model.
展开▼
