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An oblique shock wave is generated with a wave angle of \({30^ \circ }\) in a Mach \(4\) flow, at …
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A flow passes through a normal shock wave has a pressure, temperature and Mach number of \(1\,atm,\,295\,K\) and \(2.8\) upstream …
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Find the speed of sound in air at a temperature of 250 K.
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Find the stalling speed of an airplane which has a wing area of \(17\,m^2\) and is flying at sea level …
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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 are angle of attack, absolute angle of attack and induced angle of attack?
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What is the difference between symmetrical and asymmetrical /cambered airfoil?
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Define airfoil terminology and NACA series of airfoil nomenclature.
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What is flaps and what are they used for?
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What is rate of climb and turn rate of an aircraft?
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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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The BD-5J is equipped with plain flaps. The airfoil section at the wing root is an NACA 64-212, and interestingly enough, it has a thicker section at the tip, an NACA 64-218.
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For the BD-5J, calculate (a) The maximum value of CL/CD (b) The maximum value of CL^(1/ 2) /CD
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