Thin symmetrical airfoils with an angle of attack of 1.5 are considered. According to the calculation results

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Thin symmetrical airfoils with an angle of attack of 1.5° are considered. According to the calculation results of thin airfoil theory, try to calculate the lift coefficient and moment coefficient of the leading edge.

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Aerodynamics

ISBN: 9789811945861

1st Edition

Authors: Peiqing Liu

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