Experimental Study of Shock Wave Oscillation on SC(2)-0714 Airfoil
نویسندگان
چکیده
An experimental study executed in the NPU NF-6 transonic wind tunnel on shock oscillations over SC(2)-0714 airfoil is presented. Tests are conducted at freestream Mach number from 0.72 to 0.82, Reynolds number based on the airfoil chord change from approximating 3.0 million to 5.0 million with transition strip fixed at 28% chord length. Limited span wise pressure distributions are obtained to verify the two-dimensionality of the flow field. The unsteady pressures on upper surfaces are analyzed and transonic buffet onset points are given. The results show that the phenomenon is essentially two dimensional in the middle of the model. The effect of the Reynolds number is negligible when the difference is about 1 million. Finally Lee’s self-sustained shock oscillation model is examined.
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