Progress in Control Actuators for Dynamic Stall Alleviation. G.U. Aero Report 9919

Whyte, V. (1999) Progress in Control Actuators for Dynamic Stall Alleviation. G.U. Aero Report 9919. Technical Report. Department of Aerospace Engineering, University of Glasgow.

Abstract

Summary: This paper reports on a continuing investigation into trailing edge actuators for use in dynamic stall alleviation. A discrete vortex code is used to model the flow over a NACA 0015 section as it pitches from 0 to 40 degrees at pitch rates from 0.0266 to 0.0974. Various static actuators have been modelled, including a blunted trailing edge, notches of varying depths, and trailing edge flaps. These experiments show that static actuators do not have enough of an affect on the flow over the airfoil to provide an effective solution. This investigation will therefore continue by investigating the use of dynamically moving actuators.

• Item Type: Research Reports or Papers (Technical Report)
• Additional Information: University of Glasgow author: V. Whyte.
• Status: Published
• Glasgow Author(s) Enlighten ID: UNSPECIFIED
• Authors: Whyte, V.
• College/School: College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
• Publisher: Department of Aerospace Engineering, University of Glasgow
• Copyright Holders: Copyright © 1999 Department of Aerospace Engineering, University of Glasgow
• Publisher Policy: Reproduced with the permission of the Department