Accession Number:

AD0265887

Title:

LOW SUBSONIC PRESSURE DISTRIBUTIONS ON THREE RIGID WINGS SIMULATING PARAGLIDERS WITH VARIED CANOPY CURVATURE AND LEADING-EDGE SWEEP

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

• FOURNIER,PAUL G.
• BELL,B. ANN

Report Date:

1961-11-01

Pagination or Media Count:

1.0

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

Descriptors:

• *SUBSONIC FLOW
• *THERMONUCLEAR REACTIONS
• AIRCRAFT MODELS
• CURVED PROFILES
• DELTA WINGS
• EXPERIMENTAL DATA
• PHASE MEASUREMENT
• PHOTOGRAPHS
• TRANSONIC WIND TUNNELS

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE