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A finite wing with an elliptical lift distribution has an aspect ratio of \(6\). The airfoil of the wing has …
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A finite wing has aspect ratio of \(6\) and taper ratio of \(0.8\). The airfoil constituting this wing has a …
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A NACA 4421 airfoil having a chord length of \(2\,m\) is flying at an velocity of \(70\,m/s\) at an altitude …
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An airfoil has a lift coefficient and moment coefficient of \(-0.35\) and \(-0.050\) about quarter-chord at \(-6^{\circ}\) angle of attack. …
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A NACA 0012 airfoil having a chord of \(2.3\,m\) is in an airstream velocity of \(70\,m/s\) at standard sea level …
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A positively cambered airfoil has a zero-lift angle of \(-3.5^{\circ}\). The lift slope for this airfoil is \(0.12\) per degree. …
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Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of \(8^{\circ}\) …
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What are angle of attack, absolute angle of attack and induced angle of attack?
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What is lift and drag coefficients?
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The Cessna Cardinal, a single-engine light airplane, has a wing with an area of 16.2 m2 and an aspect ratio of 7.31. Assume that the span efficiency factor is 0.62.
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