Investigation of the Leading Edge Flap Effects on the Aerodynamic Coefficients of a Cranked Arrow Delta Wing

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Karimshahian Bidgoli, Alireza | 2018

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 51667 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Soltani, Mohammad Reza
Abstract:
In this study, investigated the simulation flow over a double-delta wing. The flow field was simulated by three dimension grid and RANS flow equation by K-ω-SST model. In order to investigate effect of AOA and leading edge flap simulated variable AOA and leading edge flap angle. The results shows created two vortex in inside and outside the wing. The vortex burst at high AOA and the Lift decrease after vortex bursting. The using leading edge flap effect on the vortex power and postpone vortex bursting and increasing wing lift coefficient in the high AOA. Also the leading edge flap effect on the pitch moment coefficient and change the pitch moment coefficient curve slope. The other effects of the leading edge reducing drag coefficient, increasing Lift to drag ratio and reducing approach speed
Keywords:
Delta Wing ; Leading Edge Vortex ; Vortexs ; Separation ; Lift Coefficient ; Stalling ; Aerodynamic Coefficient

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