TECNOLOGIA AEROESPACIAL I TRANSPORT AERI (Curs Total)
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At a given altitude, the drag power for a certain propeller-powered airplane of mass m = 1000 kg is given by Pr = 0.10 v3 + 0.04 W2/v (where v is given in ms−1), and the available engine power can be considered independent of speed and approximately Pa = 120 kW. What is the maximum rate of climb (R/C) this airplane can achieve at this altitude? (take g ≅ 10 ms−2)
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Why should we wait for a while after setting the flight parameters to the next data point before starting records?
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If we are to keep altitude constant, which flight parameter and between which extreme values would you choose to set?
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Which atmospheric parameter do we need to convert indicated airspeed (VIAS) to true airspeed (VTAS)
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Which of the following conditions is crucial to the success of the experiment if we can measure everything that we have discussed above?
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Which atmospheric parameter and airplane geometrical parameter are necessary to complete the derivation of CL and CD?
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Which equations would you use to derive the necessary forces from those we have access to?
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To which forces do you think we have access (we can measure) during the flight test?
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Which of the attitude parameters do we need if we choose the simplest equilibrium for our test flight?
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Which of the following aerodynamic parameters do we need in addition to the previously mentioned forces to derive CL and CD?
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