Paul W. Harper, Roy E. Flanigan
A wind-tunnel investigation was conducted of a one-twentieth-scale partial model of a conventional fighter airplane to determine the affects of rate of change of angle of attack on its maximum lift. The test were intended to supplement previous tests of the same model by extending the range of variables. The present test covered a Mach number range from approximately 0.10 to 0.80 at pitching velocities varying from nearly 0 to about 20 radians per second.
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