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An airfoil generates a lift of 80 N when operating in a free stream flow of 60 m/s.If the ambient …
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A rocket motor has a combustion chamber temperature of 2600 K and the products have molecular weight of 25g/mol and …
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- 1 answers
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A thin long circular pipe of 10 mm diameter has porous walls and spins at 60 rpm about its own …
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- 1 answers
- 0 votes
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The logarithmic decrement measured for a viscously damped single degree of freedom system is 0.125.What is the value of the …
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- 1 answers
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What is the ratio of flight speed to the exhaust velocity for maximum propulsion efficiency ?
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What is the Mach angle for a flow at Mach 2.0 ?
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If an aircraft takes-off with 10 % less fuel in -comparison to its standard configuration,how its range will vary.
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The stagnation temperatures at the inlet and exit of a combustion chamber are 600 K and 1200 K ,respectively.If the …
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How buckling of the fuselage skin can be delayed ?
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The propellant in a single stage sounding rocket occupies 60 % of its initial mass.If all of it is expanded …
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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 at an angle of attack of \(5^{^{\circ}}\), using linearized theory.
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