Calculate the lift force generated by a NACA 1408 airfoil with a chord of (1.5 mathrm{~m}) and

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Calculate the lift force generated by a NACA 1408 airfoil with a chord of \(1.5 \mathrm{~m}\) and a span of \(15 \mathrm{~m}\) operating at \(50 \mathrm{~m} / \mathrm{s}\) and an angle of attack of 8 degrees in air at a temperature of \(20^{\circ} \mathrm{C}\) and a pressure of \(1 \mathrm{~atm}\). The kinematic viscosity of air at \(20^{\circ} \mathrm{C}\) is \(15.11 \times 10^{-6} \mathrm{~m}^{2} / \mathrm{s}\).

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Fundamentals Of Aerodynamics ISE

ISBN: 9781266076442

7th Edition

Authors: John D. Anderson, Jr, Christopher P Cadou

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