02528nam a2200469Ia 4500011448575MiAaHDL20141009010000.0m d cr bn ---auaua070417s1961 dcua bt f000 0 eng d19980228464sdr-uiuc6395626(OCoLC)123193590FERFERUIUUL-1757Fournier, Paul G.Low subsonic pressure distributions on three rigid wings simulating paragliders with varied canopy curvature and leading-edge sweep /by Paul G. Fournier and B. Ann Bell.Washington, [D.C.] :National Aeronautics and Space Administration,1961.51 p. :ill. ;26 cm.NASA technical note ;D-983Report Number: L-1757.Document ID: 19980228464."NASA TN D-983.""Langley Research Center, Langley Air Force Base, Va.""November 1961."Cover title.Includes bibliographical references (p. 4).An investigation has been 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°. Three rigid metal models simulated a 45° basic flat planform paraglider with leading-edge sweep angles of 61.6°, 52.5°, and 48.6°. These configurations resulted in one-half-circle, one-third-circle, and one-quarter-circle semispan trailing-edge curvature when viewed from downstream. The results of the investigation are presented as curves of chordwise pressure distributions at four spanwise locations.Also available from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 4/09/07: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19980228464_1998393854.pdf.Mode of access: Internet.Trailing edges.nasatAngle of attack.nasatTransonic wind tunnels.nasatRigid wings.nasatPlanforms.nasatPressure distribution.nasatParagliders.nasatCircles (Geometry)nasatLeading edge sweep.nasatBell, B. Ann.United States.National Aeronautics and Space Administration.Langley Research Center.01144857520101104160837.020141009010000.020141112165512.02025-01-02T19:13:47Z2025-01-02T18:30:02ZSDR-UIUCUNKNOWNloader.pl-003-020BKsdr-uiuc6395626uiugSDRUIUCuiug.30112106914853UIU6395626UIUUIUC20250102googleuiug.301121069148531961pdbibUS fed doc