PPRuNe Forums - View Single Post - C l max affected by camber of airfoil
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Old 28th Sep 2018, 12:35
  #5 (permalink)  
Join Date: Sep 2005
Location: italy
Posts: 42
Hi thanks for your reply
I do understand the reason behind the increase in lift due to the usage of the TE flaps, however i am having a hard time understanding why the CL max would increase - is it because a given AOA will generate a greater lift causing the whole lift curve to shift upwards resulting in all the CL to move up and thus the CLmax as well?


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