EXPERIMENTAL INVESTIGATION OF 3-DIMENSIONAL DYNAMIC STALL MODEL OSCILLATING IN PITCH

The ONERA semiempirical theoretical model for unsteady aerodynamics in the stall regime has been extended to three-dimensional flow. Paramet er identification for the model is obtained from experimental dynamic stall data for a low AR rectangular wing with a NACA 0012 airfoil prof ile oscillating in pitch. Excellent correlations were obtained with th e measured data for a three-dimensional linear aerodynamic model and r easonable agreement between theory and test data were obtained for a n onlinear (stalled) aerodynamic model. Qualitatively, the results obtai ned for this simple three-dimensional wing are similar to the correspo nding data for the two-dimensional airfoil.