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GATE 2024 AE – Question 35

Aerodynamics · Airfoils and wings: coefficients, Kutta-Joukowski theorem, thin airfoil theory, finite wing theory, critical and drag divergence Mach numbers · 1 mark · Numerical answer

Using thin airfoil theory, the lift coefficient of a NACA 0012 airfoil placed at $5^o$ angle of attack in a uniform flow is _____________ (rounded off to 2 decimal places).

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Correct answer: 0.54 to 0.56

Explanation

The NACA 0012 is symmetric, so $\alpha_{L=0} = 0$ and thin airfoil theory gives $c_l = 2\pi\alpha = 2\pi \times \frac{5\pi}{180} = 0.548$.