Show that the solution of thin airfoil theory of a symmetric airfoil given below satisfies the Kutta condition. What angle of at
tack 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
1 answer:
Answer:
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.
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Answer:
(a) 53.94%
(b) 26.61%
Explanation:
Change in area will be given by
where
represent change in area R is radius and subscripts O and n represent original and new respectively.
Substituting 10.55/2 for original radius and 7.16/2 for new radius then
(b)
Similarly, percentage elongation will be found by dividing the change in length by the the original length. In this case, rhe original length was 54.5mm and goes to 69 mm so the change in length is given by subtracting the final length from the original length
Percentage elongation is