The preference for closed-test-section wind tunnels, that offer superior flow quality, reduced significantly work and research carried out in open-jet wind-tunnel facilities in the 20th century. The advantages offered by open-jet test sections for aeroacoustic testing, recaptured the interest of experimentalists for open-jet facilities in the last decades. While experimental campaigns may be aimed at aeroacoustics, aerodynamic performance is generally also of relevance. The wind tunnel corrections for aerodynamic measurements on airfoils in open-jet wind tunnels are not sufficiently understood. In this paper an approach is presented to calculate drag, lift and effective angle of attack from the wake of an airfoil in a 2D open-jet wind-tunnel flow. PIV measurements in the wake of the DU-96-W-180 airfoil have been performed at Reynolds Numbers 0.5 × 10~6 and 0.63 × 10~6. The experimental results for lift and drag differed less than 3% and 9%, respectively, compared to data obtained in a closed test section facility.
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