Accession Number : ADA298170
Title : Summary of Measurements in Langley Full-Scale Tunnel of Maximum Lift Coefficients and Stalling Characteristics of Airplanes,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC
Personal Author(s) : Sweberg, Harold H. ; Dingeldein, Richard C.
PDF Url : ADA298170
Report Date : 1945
Pagination or Media Count : 42
Abstract : The results of measurements in the Langley full-scale tunnel of the maximum lift coefficients and stalling characteristics of airplanes have een collected. The data have been analyzed to show the nature of the effects on maximum lift and stall of wing geometry, fuselages and nacelles, propeller slipstream, surface roughness, and wing leading-edge appendages such as ducts, armaments, tip slats, and airspeed heads. Comparisons of full-scale-tunnel and flight measurements of maximum lift and stall are included in some cases and the effects of the different testing techniques on the maximum-lift measurements are also given. The results indicated that large improvements in the maximum lift and stalling characteristics of airplanes can be obtained by careful attention to detail design. Surface roughness, wing leakage, and the improper location of ducts, armament, and slats at the leading edge of a wing have been found to cause serious losses in the maximum lift coefficient of an airplane. Wings having higher taper ratios and large amounts of sweepback have been shown to be subject to poor stalling characteristics because they are susceptible to tip stalling. (AN)
Descriptors : *STALLING, *AERODYNAMIC LIFT, AIR FLOW, SURFACE ROUGHNESS, ANGLE OF ATTACK, FUSELAGES, WIND TUNNEL TESTS, FLOW SEPARATION, WING BODY CONFIGURATIONS, REYNOLDS NUMBER, BOUNDARY LAYER FLOW, SPLIT FLAPS, AERIAL PROPELLERS, LEADING EDGE FLAPS.
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE