Using thin-airfoil theory, find the magnitude of the leading-edge pitching-moment coefficient for a symmetric airfoil at angle of attack 10° (two decimal places).
For a symmetric thin airfoil, $C_l=2\pi\alpha$ and $C_{m,c/4}=0$. Translating the moment reference to the leading edge gives $C_{m,LE}=-C_l/4=-\pi\alpha/2$. With α=10π/180 rad, its magnitude is 0.2742, or 0.27.
More Airfoils and wings: coefficients, Kutta-Joukowski theorem, thin airfoil theory, finite wing theory, critical and drag divergence Mach numbers questions
GATE 2019 AE Q49– A finite wing of span b=10 m has circulation (y)= 01-(2y/b)2, with Γ₀=20 m²/s. Free-stream…
GATE 2024 AE Q24– Consider steady, incompressible, inviscid flow past two airfoils shown in the figure. The…
GATE 2024 AE Q35– Using thin airfoil theory, the lift coefficient of a NACA 0012 airfoil placed at 5o angle…
GATE 2024 AE Q64– An airplane of mass 1000 kg is in a steady level flight with a speed of 50 m/s. The wing…
GATE 2025 AE Q18– For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length…
GATE 2025 AE Q19– A positively cambered airfoil is placed in a uniform flow (velocity, U ) at its zero-lift…