EXPERIMENTAL INVESTIGATION OF SHOCK WAVE OSCILLATION ON A THIN AIRFOIL

Document Type: Article

Authors

1 Faculty of New Sciences and Technologies, University of Tehran, Tehran, 1417614418

2 Department of Aerospace Engineering, Sharif University of Technology, Azadi Ave., Tehran, 11365-11155, Iran

Abstract

Experimental results of surface pressure distribution over a thin supercritical airfoil and its wake are presented. All tests were conducted at free stream Mach numbers from 0.27 to 0.85 and at different angles of attacks in a transonic wind tunnel. The model was equipped with static pressure orifices connected to high frequency pressure-transducers. The present paper evaluates variations of shock wave location with both Mach number and angle of attack variation as well as its interaction with the boundary layer leading to the buffet phenomenon. The frequency of the shock wave oscillation and unsteady wake behaviour at a freestream Mach no. of M=0.6 and at different angles of attacks are measured using cross-correlation technique by means of pressure sensors locating on the suction side of the model and via the rake total pressure data that was traversed vertically behind the model respectively. From the analysis of surface pressure distribution and wake data, drag divergence occurred at a certain angle of attack and at a frequency equal to the shock wave oscillation frequency.

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