The dynamic stall characteristics of a slatted airfoil were investigated experimentally on a 2-ft-chord airfoil oscillating in pitch at M = 0.2 for a range of reduced frequency and mean angle of oscillation. The slat produced a flow that remained attached to the airfoil for angles well above those normally attained by the retreating blade of a helicopter during high speed flight. The dynamic stall vortex usually associated with these flight conditions was completely eliminated for all angles under 30 deg. Instantaneous surface pressure, lift, and pitching moment data are presented as a function of incidence throughout the oscillation cycle; a detailed analysis of instantaneous boundary-layer flow behavior for the various test conditions is included.
The effect of a leading-edge slat on the dynamic stall of an oscillating airfoil
1983-10-01
Conference paper
No indication
English
Leading-edge slat optimization for maximum airfoil lift
TIBKAT | 1979
|Dynamic stall of an oscillating airfoil
NTRS | 1978
|Oscillating Airfoil Compressible Dynamic Stall Studies
British Library Conference Proceedings | 1993
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