1950•NASA Technical Reports Server (NASA)Requires access
The effect of rate of change of angle of attack on the maximum lift of a small model
Paul Harper, Roy E. Flanigan
Open publisher page 27 citations
Abstract
Report presenting a wind-tunnel investigation of a partial model of a conventional fighter airplane to determine the effects of rate of change of angle of attack on its maximum lift. The results indicated that the maximum lift coefficient increased linearly with pitching velocity up to a limit value of the lift coefficient which depended on the Mach number.