LOW SUBSONIC PRESSURE DISTRIBUTIONS ON THREE RIGID WINGS SIMULATING PARAGLIDERS WITH VARIED CANOPY CURVATURE AND LEADING-EDGE SWEEP
Abstract
An investigation was made in the Langley 7- by 10-foot transonic tunnel to determine the subsonic pressure distribution of three paraglider models through an angle-of-attack range from 0 to 74 degrees. Three rigid meta models simulated a 45 degrees basic flat planform paraglider with leading-edge sweep angles of 61.6, 52.5 and 48.6 degrees. These configurations resulted in one-half-circle, one-third-circle, and one-quarter-circle semispan trailing-edge curvature when viewed from downstream. The results are presented as curves of chordwise pressure distributions at four spanwise locations. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1961
- Accession Number
- AD0265887
Entities
People
- B. Ann Bell
- Paul G. Fournier
Organizations
- National Aeronautics and Space Administration