Investigation of the Variation of Maximum Lift for a Pitching Airplane Model and Comparison with Flight Results

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 investigations of a l% scale model of a conventional single-engine fighter airplane and were 20 compared with existing flight data for this airplane. The wind-tunnel investigation extended through a Mach number range from approximately 0.2 to 0.6 at pitching velocities comparable to flight values obtained with the test airplane in abrupt pull-ups. The wind-tunnel and flight results were found to be in good agreement.