Behavior of airfoil with control surface freeplay for nonzero angles of attack


Journal Article

The behavior of a three-degree-of-freedom typical airfoil is studied by numerical time integration using a standard state-space approximation, focusing on the effects of the mean or steady angle of attack. A variety of behavior is observed and the main tendency displayed by the system as the angle of attack increases is the transition from the predominance of limit cycle oscillations to a static deflection. The magnitude of the flap motion is of the order of the freeplay gap δ. For a typical airfoil, δ is 1 degree or less. Similarly, the pitch motion is of the order of the δ, and the plunge motion is of the order of the δ times airfold chord. Hence, the motions involved are sufficiently small that classical linear aerodynamic theory is still valid.

Full Text

Duke Authors

Cited Authors

  • Kholodar, DB; Dowell, EH

Published Date

  • January 1, 1999

Published In

Volume / Issue

  • 37 / 5

Start / End Page

  • 651 - 653

International Standard Serial Number (ISSN)

  • 0001-1452

Digital Object Identifier (DOI)

  • 10.2514/2.766

Citation Source

  • Scopus