Consider an airfoil with a mean camber line as below: for 0 0.4 [025 [0-(:)]...

 

Transcribed Image Text:

Consider an airfoil with a mean camber line as below: for 0 ≤ ≤0.4 [025 [0²-(:)] [0.11 [02+0.8²-()] for0.451 419 Determine: a) The angle of attack of zero lift. b) The lift coefficient at an angle of attack of 2°. Consider an airfoil with a mean camber line as below: for 0 ≤ ≤0.4 [025 [0²-(:)] [0.11 [02+0.8²-()] for0.451 419 Determine: a) The angle of attack of zero lift. b) The lift coefficient at an angle of attack of 2°.