The aerodynamic design of a winglet for the Dassault Falcon 10 business jet was carried out. The design space was explored through vortex lattice method models, calibrated with respect to wind tunnel data. The best configuration was then analyzed with RANS and a finite element model of the original wing box was created (validated with respect to test data) to determine the weight penalty that the structural reinforcement due to the new loads would require. The aircraft performance was then calculated and compared to the baseline aircraft. Net drag reductions of 4.8% at Mach 0.7 and 2.5% at Mach 0.8 were found. The range was increased by 66 NM (4.3%) and for a 1,200 NM mission, fuel burn was reduced by 3.9%.
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