TECNOLOGIA AEROESPACIAL I TRANSPORT AERI (Curs Total)
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An airplane in straight and level flight at sea level (air density ρ = 1.225 kgm−3) has mass m = 4500 kg, wing projected area S = 20 m2 and Oswald factor e = 0.90. The lift curve is CL = 0.2 + 0.2α (angle of attack in degrees), with stall angle of attack αS = 10o. In this situation, α = 0.633o. The required power is given by Pr = 0.12 v3 + 2 107/v (v in ms−1). Taking g = 10 ms−2, what are the approximate speed and flight regime?
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The engine of an airplane produces a power Pa independent of speed. If the drag power is Pr, then...
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An airplane with mass m=1000 kg is performing an equilibrium climb with an angle trajectory γ = 4.78o at a speed v = 60 ms−1. If the drag power in this situation is Pr = 100 kW, how much engine power will be required Pa?
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The aerodynamic speed for maximum range of a reciprocating-engine-powered propeller airplane is...
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The speed for maximum range of a propeller-powered airplane...
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What are the minimum and maxmum speed in straight and level flight at sea level (ρ = 1.225 kgm−3) for a jet-powered airplane of mass m = 4000 kg, drag curve D = 0.75 v2 + 0.04 W2/v2 , and maximum available thrust T = 20000 N? Omit any consideration regarding stall.
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A piston-engined airdcraft cruising at constant altitude is flown at constant available power throughout the flight. The airplane is flying faster than the speed for maximum endurance. Then we can claim that...
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Which of the following statements is correct for a turbojet airplane?
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A cruising propeller-powered aircraft has a drag power curve Pr = av3 + bW2/v, with a and b constants, v the airplane speed and W its weight. What is the expected required power increase ∆Pr for a coordinated banked turn with roll angle ϕ if altitude and speed are to be preserved?
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For a propeller powered airplane, the power required to sustain flight at a given altitude is given by PR = 0.10 v3 + 0.16 W2/v. What is the speed for maximum endurance if the airplane's mass is m = 1000 kg?
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