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- W2325806597 abstract "The design of a winglet for the Dassault Falcon 10 business jet is presented. The configuration showing the best compromise between induced drag reduction, parasite drag and structural weight increase was selected, where the design variables were winglet span and cant angle. For the determination of the best configuration, the change in drag was calculated using a vortex lattice method model of the aircraft, calibrated with respect to wind tunnel data and the weight penalty was estimated using empirical methods. For that winglet geometry, a RANS model was created and used to generate the aircraft drag polars. Also, a finite element model of the wing box, validated with respect to stress data, was used to estimate the structural reinforcement that the new winglet loads would require and, hence, their weight penalty. Using the new drag polars and structural weights, the aircraft range and fuel burn were calculated and compared to the baseline aircraft. At typical cruise lift coefficients, the net drag reduction was 4.8% at Mach 0.7 and 2.5% at Mach 0.8. For typical operation conditions, the range was increased by 66 NM (4.3%) and for a 1,200 NM mission, fuel burn is reduced by 3.9%. The maximum range increase and fuel savings were 3.3% and 3.8%, respectively." @default.
- W2325806597 created "2016-06-24" @default.
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- W2325806597 date "2016-01-02" @default.
- W2325806597 modified "2023-09-25" @default.
- W2325806597 title "Aerodynamic Design of a Winglet for the Dassault Falcon 10" @default.
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- W2325806597 doi "https://doi.org/10.2514/6.2016-0776" @default.
- W2325806597 hasPublicationYear "2016" @default.
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