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sand0380 August 16, 2011 08:18

problem with cl coefficient
i am trying to solve model of a slotted and split flap model and i used the wing dimensions same as for Boeing 737. i have sucefully meshed it. when i import in fluent and try to solve it i get the cl interms of 14000.00, i tried all possible ways. my input conditions are. velocity 100m/s at 4degrees angle of attack, viscous model is k-e model and the refeernce values are all given except enthalpy, depth and sepcific ratio. i can't understand the problem with it. i would like to hear some advice

thank you

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