Free-flight measurements at Mach numbers from 0.7 to 1.6 of some effects of airfoil-thickness distribution and trailing-edge angle on aileron rolling effectiveness and drag for wings with 0 and 45 degrees sweepback Page: 1 of 65
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U:FREE -FLIGHT MEASUREMENTS AT MACH NUMBERS FROM 0.7 TO 1.6
OF SOME EFFECTS OF AIRFOIL-THICKNESS DISTRIBUTION AND
TRAILING-EDGE ANGLE ON AILERON ROLLING EFFECTIVENESS
AND DRAG FOR WINGS WITH 00 AND 450 SWEEPBACK
By E. M. Fields and H. Kurt Strass
Langley Aeronautical Laboratory
Langley Field, 'Va.NATIONAL ADVISORY COMMITTEE
FOR AERONAUTICS
WASHINGTON
October 8, 1951ti-j ,'
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Fields, E. M. & Strass, H. Kurt. Free-flight measurements at Mach numbers from 0.7 to 1.6 of some effects of airfoil-thickness distribution and trailing-edge angle on aileron rolling effectiveness and drag for wings with 0 and 45 degrees sweepback, report, October 8, 1951; (https://digital.library.unt.edu/ark:/67531/metadc58871/m1/1/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.