Consider the symmetric airfoil with trailing edge flap as follow. With trailing edge flap, lift coefficient...

 

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Consider the symmetric airfoil with trailing edge flap as follow. With trailing edge flap, lift coefficient of airfoil can be increased as Ac = 2[T – 6 + sin o]n where o is a variable related with flap hinge location, n is deflection angle of trailing edge. Derive the above equation and compare with simple symmetric airfoil without flap. V x = 0.8c Consider the symmetric airfoil with trailing edge flap as follow. With trailing edge flap, lift coefficient of airfoil can be increased as Ac = 2[T – 6 + sin o]n where o is a variable related with flap hinge location, n is deflection angle of trailing edge. Derive the above equation and compare with simple symmetric airfoil without flap. V x = 0.8c