Experimental and Computational Studies of Dynamic Stall
The use and control of dynamic stall has become an important factor in both aircraft and helicopter design. At the present time, dynamic stall has limited, rather than enhanced, helicopter flight. At the same time, retention of the dynamic lift that occurs when aircraft rapidly pitch past the static stall angle is critical if the full benefit of this lift augmentation for improved aircraft maneuverability is to be achieved. Thus, the alleviation of unwanted aspects of dynamic lift, and the control and augmentation of the positive aspects of this dynamic lift condition, become major research goals.
KeywordsMach Number Lift Coefficient Boundary Layer Equation Pitching Moment Inviscid Flow
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