Show that the solution of thin airfoil theory of a symmetric airfoil given below satisfies the Kutta condition. What angle of attack is required to develop a sectional lift coefficient of 0.5. Using the circulation distribution for the symmetric thin airfoil, calculate the sectional pitching moment about a point 0.5 chord from the leading edge. gamma(theta) = 2 alpha U_ infinity 1 + cos theta/sin theta

The kutta condition is satisfied

Explanation:

Thin airfoil theory: This can be described as a simple theory of airfoils that relates angle of attack to lift for incompressible, inviscid flows.

The theory simply puts the idea that the flow around an airfoil is as two-dimensional flow around a thin airfoil. It can be imagined as addressing an airfoil of zero thickness and infinite wingspan.

kindly check attachment for the calculation of the sectional pitching moment about a point 0.5 chord from the leading edge.gamma(theta) = 2 alpha U_ infinity 1 + cos theta/sin theta.

explanation:

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