Author : Paul W. Harper,Roy E. Flanigan
Publisher : Unknown
Page : 706 pages
File Size : 47,9 Mb
Release : 1948
Category : Airplanes
ISBN : STANFORD:36105024795820
Investigation of the Variation of Maximum Lift for a Pitching Airplane Model and Comparison with Flight Results by Paul W. Harper,Roy E. Flanigan Pdf
Apparatus was developed which utilized a pitching airplane model to determine maximum wing loads as a function of the rate of change of angle of attack. In order to evaluate the pitching-model technique, the maximum lift coefficient was determined as a function of the rate of change of angle of attack over a Mach number range from approximately 0.2 to 0.6 in wind-tunnel tests of a 1/20-scale model of a conventional single-engine fighter airplane and was conpared with existing flight data of this airplane. The wind-tunnel and flight results were found to be in good agreement.