Abstract
Stereoscopic Particle Image Velocimetry (SPIV) measurements have been performed on an unmanned combat air vehicle (UCAV) wind tunnel model (DLR F17E) in the DNW-TWG transonic wind tunnel. The DLR F17E model is equipped with ducted engine air intake. The model has a leading edge sweep angle of 53 deg. At various streamwise locations SPIV results have been obtained for the investigation of the flow field phenomena induced by the ducted engine air intake. In addition, flow features in the exhaust region are also obtained. The SPIV measurements are part of a project dedicated to the validation of computational codes.
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