Investigation of the variation of maximum lift for a pitching airplane model and comparison with flight results

Paul W. Harper, Roy E. Flanigan
naca-tn-1734
Oct 1948


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, maximum lift coefficients were determined in wind-tunnel investigation of 1 20th-scale model of a conventional single-engine fighter airplane and were compared with existing flight data for this airplane.

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