Consider the symmetric airfoil with trailing edge flap as

Consider the symmetric airfoil with trailing edge flap as follow. With trailing edge flap, lift coefficient of airfoil can be increased as + sin φ1η where φ is a variable related with flap hinge location, η is deflection angle of trailing edge. Derive the above equation and compare with simple symmetric airfoil without flap. x 0.8c 


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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