Last Updated On [03-11-2023]
For a symmetric airfoil at an angle of attack of $10^{\circ}$, assuming thin airfoil theory, the magnitude of the pitching moment coefficient about the leading edge is________ (round off to 2 decimal places).
Question ID - 155468 :- For a symmetric airfoil at an angle of attack of $10^{\circ}$, assuming thin airfoil theory, the magnitude of the pitching moment coefficient about the leading edge is________ (round off to 2 decimal places).
For a symmetric airfoil at an angle of attack of $10^{\circ}$, assuming thin airfoil theory, the magnitude of the pitching moment coefficient about the leading edge is________ (round off to 2 decimal places).
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The span-wise distribution of circulation over a finite wing of $\operatorname{span} b=10 \mathrm{~m}$ is $ \Gamma(y)=\Gamma_{0} \sqrt{1-\left(\frac{2 y}{b}\right)^{2}} $ If $\Gamma_{0}=20 \mathrm{~m}^{2} / \mathrm{s}$ and the free stream density and speed are $1.2 \mathrm{~kg} / \mathrm{m}^{3}$ and $100 \mathrm{~m} / \mathrm{s}$, respectively, the total lift is _________$\quad \mathrm{kN}$ (round off to 2 decimal places).
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