Experimental investigation of three-dimensional dynamic stall model oscillating in pitch


Journal Article

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.

Full Text

Duke Authors

Cited Authors

  • Tang, DM; Dowell, EH

Published Date

  • January 1, 1995

Published In

Volume / Issue

  • 32 / 5

Start / End Page

  • 1062 - 1071

International Standard Serial Number (ISSN)

  • 0021-8669

Digital Object Identifier (DOI)

  • 10.2514/3.46837

Citation Source

  • Scopus