What is the section lift coefficient

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Reference no: EM13216826

Consider a NACA 0009 airfoil that has a plain flap whose length is 0.2c and which is deflected 25. a. Calculate cl and cmc/4 When the geometric angle of attack is 4 degrees, what is the section lift coefficient? Where is the center of pressure?

Reference no: EM13216826

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What is the section lift coefficient : Consider a NACA 0009 airfoil that has a plain flap whose length is 0.2c and which is deflected 25. a. Calculate cl and cmc/4 When the geometric angle of attack is 4 degrees, what is the section lift coefficient? Where is the center of pressure?

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