Experimental investigation of three-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. Parameter identification for the model is obtained from experimental dynamic stall data for a low AR rectangular wing with a NACA 0012 airfoil profile oscillating in pitch. Excellent correlations were obtained with the measured data for a three-dimensional linear aerodynamic model and reasonable agreement between theory and test data were obtained for a nonlinear (stalled) aerodynamic model. Qualitatively, the results obtained for this simple three-dimensional wing are similar to the corresponding data for the twodimensional airfoil. © 1995 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

Duke Scholars

Author Earl H. Dowell Thomas Lord Department of Mechanical Engineering and Materia ...