PPRuNe Forums - View Single Post - C l max affected by camber of airfoil
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Old 28th Sep 2018, 13:13
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washoutt
 
Join Date: Apr 2015
Location: Netherlands
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A flap extension with zero flap angle will increase the lift L, not necessarily the lift co-efficient CL. When the extended flap are turned down with a certain angle, only then will the circulation increase, as Dook says. This will lead to a higher CL max.
I am not sure whether extension of slats have no effect on CL max, I would think that with an increase in AOA the circulation will increase at higher AOA, and therefor resulting in a higher CL max.
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