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Old 11th Apr 2012, 22:23
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Anders S
 
Join Date: Jun 2010
Location: Stockholm
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Obviously I'm missing something, but hopefully some one here can help me out.

Question 1:
Given that the characteristics of a three engine turbojet aeroplane are as follows:
Trust = 50000 N per engine
g= 10 m/sē
Drag = 72569 N
Minimum gross gradient (2nd segment) = 2.7%
The maximum take-off mass under segment 2 conditions in the net take-off flight path conditions is:

a. 101596 kg
b. 286781 kg
c. 74064 kg
d. 209064 kg

Question 2:
The determination of the maximum mass on brake release, of a certified turbojet aeroplane with 5°, 15° and 25° flaps angles on take-off, leads to the following values, with wind:

Flap angle: 5° 15° 25°
Runway limitation: 66000 69500 71500
2nd segment slope limitation: 72200 69000 61800

Wind correction: Head wind: + 120 kg per kt OR tail wind: -360 kg per kt
Given that the tail wind component is equal to 5 kt, the maximum mass on brake release and corresponding flap angle will be:

a. 67700/15°
b. 69000/15°
c. 72200/5°
d. 69700/25°

Question 3:
On a segment of the take-off flight path an obstacle requires a minimum gradient of climb of 2.6% in order to provide an adequate margin of safe clearance. At a mass of 110000 kg the gradient of climb is 2.8%. For the same power and assuming that the angle of climb varies inversely with, at what maximum mass will the aeroplane be able to to achieve the minimum gradient?

a. 121310 kg
b. 106425 kg
c. 118455 kg
d. 102142 kg

It's too late for me to write in my calculations, and for the same reason, please excuse any typos.

-Anders
Anders S is offline