Consider a thin, symmetric airfoil at \(1.5^{\circ}\) angle of attack. From the results of thin airfoil theory, calculate the lift coefficient and the moment coefficient about the leading edge.

Consider a thin, symmetric airfoil at \(1.5^{\circ}\) angle of attack. From the results of thin airfoil theory, calculate the lift coefficient and the moment coefficient about the leading edge.

techAir Asked on 9th November 2019 in Aerodynamics.
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    From the results of thin airfoil theory \[c_{l}=2\pi\alpha=2\pi\left ( \frac{1.5}{57.3} \right )=0.164\;\mathrm{radians}\]

    \[c_{m,le}=-\frac{c_{l}}{4}=-\frac{0.164}{4}=-0.041\]

    Worldtech Answered on 9th November 2019.
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