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Bubble78

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Lift coefficient

If the lift coefficient for a wing at a specified angle of attack is known (or estimated using a method such as thin-airfoil theory), then the lift produced for specific flow conditions can be determined using the following equation:
 L = \tfrac12\rho v^2 A C_L
where

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xDaisyChainsx
 
 Age: 26
 Long Beach, California