Numerical Study of Unsteady Flow Around Airfoil With Spoiler

[+] Author and Article Information
Cheng Xu

National Measurement Centre, Mechanical Metrology, Singapore Productivity & Standards Board, One Science Park Drive Singapore 118221

W. W. H. Yeung

School of Mechanical and Production Engineering, Nanyang Technological University, Singapore 639798

J. Appl. Mech 65(1), 164-170 (Mar 01, 1998) (7 pages) doi:10.1115/1.2789020 History: Received September 30, 1996; Revised July 24, 1997; Online October 25, 2007


A discrete vortex model based on the panel method has been developed to simulate the two-dimensional unsteady separated flow generated by the rapid deployment of a spoiler on the upper surface of an airfoil. This method represents the boundary surfaces by distributing piecewise linear-vortex and constant source singularities on discrete panels. The wake of the spoiler and airfoil is represented by discrete vortices. At each sharp edge, a vortex sheet is used to feed discrete vortices at every time-step to form the downstream wake. The length and strength of each shed vortex sheet are determined by the continuity equation and a condition such that the flow, the net force, and the pressure difference across the vortex sheet are zero. The flow patterns behind the spoiler at different time-steps are presented. The pressure distributions on the airfoil based on the unsteady Bernoulli’s equation are compared, where possible, with the experimental results and other computational results. The adverse lift effects have been obtained, and similar effects have been measured in experiments.

Copyright © 1998 by The American Society of Mechanical Engineers
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