WIT Press


An Experimental Investigation Of The Reduced Frequency Effects Into Pressure Coefficients Of A Plunging Airfoil

Price

Free (open access)

Paper DOI

10.2495/AFM080151

Volume

59

Pages

9

Page Range

153 - 161

Published

2008

Size

663 kb

Author(s)

M. Mani, F. Ajalli & M. R. Soltani

Abstract

An experimental investigation of the reduced frequency effects into pressure coefficients of a plunging airfoil M. Mani1, F. Ajalli2 & M. R. Soltani3 1Department of Aerospace Engineering, Amirkabir University of Technology, Iran 2Aerospace Research Institute, Iran 3Department of Aerospace Engineering, Sharif University of Technology, Iran Abstract Aerodynamic coefficients on a two dimensional plunging airfoil, in a low-speed wind tunnel are presented. Dynamic motion was produced by plunging the model over a range of reduced frequencies, and mean angles of attack. The Reynolds number in the present test was held fixed ( 5 10 5 . 1 Re × = ), and the reduced frequency was varied in an almost wide range. Surface static pressure distribution was measured on the upper and lower sides of the model, during the oscillating motion. It was found that reduced frequency had strong effects on the pressure distribution, near the leading edge of the airfoil. For mean equivalent angles of attack of 0, 5 degrees, hysteresis loops on the upper surface of the airfoil near the leading edge were counter clockwise and for high mean equivalent angle they were clockwise. By increasing the reduced frequency the hysteresis loops became wider and larger. Keywords: unsteady aerodynamic, hysteresis loops, plunging airfoil, reduced frequency. 1 Introduction In many engineering applications, lifting surfaces experience unsteady motions or are perturbed by unsteady incoming flows. High level dynamic loading and noise generation are inherent problems, due to unsteadiness [1]. One of the basic

Keywords

unsteady aerodynamic, hysteresis loops, plunging airfoil, reduced frequency.