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Investigate the principles of aerodynamics in mechanical engineering, covering topics such as fluid flow around objects, lift and drag forces, …
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Consider a finite wing of aspect ratio 4 with an NACA 2412 airfoil; the angle of attack is 5°. Calculate …
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Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach \(2.5\) freestream flow …
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What are form drag and profile drag?
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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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Find the gliding distance of an aircraft flying at an altitude of \(1500\,m\) with a maximum lift to drag ratio …
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Calculate the lift, drag and moment coefficient about quarter chord per unit span of an airfoil which is at an …
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What is flaps and what are they used for?
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What is the difference between static and dynamic stability of an aircraft?
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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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Investigate the principles of aerodynamics in mechanical engineering, covering topics such as fluid flow around objects, lift and drag forces, and boundary layer phenomena.
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Consider an airplane in an accelerated climb. At a given instant in this climb, the specific excess power is 120 ft/s
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Consider an airplane flying at 620 mi/h at 35,000 ft. Calculate its energy height.
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For a turbojet-powered airplane with the altitude variation of thrust given by Eq. (3.19), show that as the altitude increases, the maximum velocity decreases.
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