02984cam a2200553Ia 4500011424420MiAaHDL20141013010000.0m d cr bn ---auaua060925s1974 dcua bt f000 0 eng d2811978119740025317N743343074N33430GBVCP607851635sdr-uiuc6359424(OCoLC)71636279FERFERABCLHLUIUUTL521.3.T4A3 no. 3060NAS 1.15:X-3060L-9327Beasley, William D.Low-speed aerodynamic characteristics of airfoil sections with rounded trailing edges in forward and reverse flow /by William D. Beasley and Robert J. McGhee.Washington, D.C. :National Aeronautics and Space Administration ;Springfield, Va. :For sale by the National Technical Information Service [distributor],1974.102 p. :ill. ;27 cm.NASA technical memorandum ;X-3060"NASA TM X-3060."Performing organization report no.: L-9327."September 1974."Cover title.Includes bibliographical references (p. 16).Low-speed wind-tunnel tests were conducted to determine the two-dimensional aerodynamic characteristics of 6-, 12-, and 18-percent-thick airfoil sections with rounded trailing edges in both forward and reverse flow. The shapes incorporated camber with both the leading and trailing edges rounded to provide reasonable aerodynamic performance with either edge directed toward the free-stream flow. The tests were conducted with the airfoils in both normal and reverse orientations relative to the free stream. The Mach number was varied from 0.16 to 0.36 and the angle of attack was varied from minus 10 to 24 million. Reynolds number, based on the airfoil chord, was varied from about 1.0 to 12.0 million.Also available online from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 9/19/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19740025317_1974025317.pdf.Performed by Langley Research Center, Hampton, Va.760-17-01-11Mode of access: Internet.Rotors (Helicopters)Aerodynamics.Rotors (Helicopters)Testing.Wind tunnel tests.nasatReversed flow.nasatAirfoil profiles.nasatAerodynamic configurations.nasatTwo dimensional flow.nasatTrailing edges.nasatSubsonic speed.nasatFree flow.nasatAirfoils.nasatAerodynamic characteristics.nasatMcGhee, Robert J.Langley Research Center.01142442020101004082745.020141013010000.020141112173021.02025-01-01T19:24:16Z2025-01-01T18:30:02ZSDR-UIUCUNKNOWNloader.pl-003-020BKsdr-uiuc6359424uiugSDRUIUCuiug.30112106659961UIU6359424UIUUIUC20250101googleuiug.301121066599611974pdbibUS fed doc--NTIS: pubdate < 2020