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yan [13]
3 years ago
10

A helicopter is hovering in a steady cross wind at a gross weight of 3,000 lb (1,360.8 kg). This helicopter has 275 hp (205 kW)

delivered to the main rotor shaft. The tail rotor is 2.3 ft (0.701 m) and has an induced power factor of 1.15. The tail rotor is located 15.3 ft (4.66 m) from the main rotor shaft. Determine the crosswind conditions (velocity and direction) in which the tail rotor effectiveness may be reduced or lost. If the center of gravity is assumed to lie on the rotor shaft axis, determine the feasible yawing angular velocity that the pilot can demand that may also result in a loss of tail rotor effectiveness
Engineering
1 answer:
damaskus [11]3 years ago
6 0

Answer: Answer Bellow

Explanation:The helicopter has 275 hp (205 kW) delivered to the main rotor shaft. The tail rotor radius is 2.3 ft (0.701 m) and has an induced power factor of 1.15.

(I would appreciate brainiest)

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Answer:

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\frac{ \Delta P}{ -g\, \rho\,}= \Delta h\\\Delta h=\frac{97.66 \, kPa}{998 kg/m^3 \, \, 9.81 m/s^2} \\\Delta h=9.975\,m

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4 years ago
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3 years ago
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2 years ago
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attached below

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For some transformation having kinetics that obey the Avrami equation (Equation 10.17), the parameter n is known to have a value
OleMash [197]

Answer:

t = 25.10 sec

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