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A thin cambered airfoil is approximated by three straight line segments as shown in the below figure. Calculate zero-lift angle of attack, coefficient of
A thin cambered airfoil is approximated by three straight line segments as shown in the below figure. Calculate zero-lift angle of attack, coefficient of lift and moment coefficient about leading edge for an angle of attack of 3 degrees. (15 Marks) Y b 0 1 334 1 X [Note: For the value of b, use your Roll number AE22M5XY. If XY < 10 then b = XY/100. If XY 10 then b = XY/1000]
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Fundamentals Of Aerodynamics
Authors: John Anderson
6th Edition
1259129918, 978-1259129919
