GATE AE concept:load-factor PYQs & Answers

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Questions 1–8 of 8. Imported answers require independent review unless marked reviewed.

Topic practice 8 questionsPage 1 of 1

An airplane experiences a net vertical ground reaction of 1500 N during landing. The weight of the airplane is 1000 N. The landing vertical load factor, defined as the ratio of inertial load to the weight of the aircraft, is ________ (rounded off to 1 decimal place).

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An airplane weighing 40 kN is landing on a horizontal runway during which it is retarded by an arresting cable mechanism. The tension in the arresting cable at a given instant, as shown in the figure, is 100 kN. Assuming that the thrust from the engine continues to balance airplane drag, the magnitude of horizontal load factor is _______. (round off to one decimal place)

Diagram for Aerospace Engineering question 32

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The maximum permissible load factor and the maximum lift force coefficient for an airplane is 7 and 2, respectively. For a wing loading of 650 N/m

and air density 1.23 kg/m

, the speed yielding the highest possible turn rate in the vertical plane is __________ m/s. (round off to the nearest integer)

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For a conventional fixed-wing aircraft in a 360° inverted vertical loop maneuver, what is the load factor (

) at the topmost point of the loop? Assume the flight to be steady at the topmost point.

Your answerChoose one option.

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An airplane of mass 5000 kg is flying at a constant speed of 360 km/h at the bottom of a vertical circle with a radius of 400 m, as shown in the figure. Assuming that the acceleration due to gravity is 9.8 m/s

, the load factor experienced at the center of gravity of the airplane is ______ (round off to two decimal places).

Diagram for Aerospace Engineering question 25

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An airplane of mass 400 kg and wing reference area 25 m² flying at sea level has a maximum lift coefficient of 1.65. Assume density of air as 1.225 kg/m³ and acceleration due to gravity as 9.8 m/s². Using a factor of safety of 1.25 to account for additional unsteady lift during a sudden pull-up, the speed at which the airplane reaches a load factor of 3.2 is ______ m/s (round off to two decimal places).

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The airplane shown in figure starts executing a symmetric pull-up maneuver from steady level altitude with a constant nose-up pitch acceleration of 20 deg/s

. The vertical load factor measured at this instant at the centre of gravity (CG) is 2. Given that the acceleration due to gravity is 9.81 m/s

, the vertical load factor measured at point P on the nose of the airplane, which is 2 m ahead of the CG, is ______ (round off to 2 decimal places).

Diagram for Aerospace Engineering question 40

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The highest limit load factor experienced by a civil transport aircraft is in the range

Your answerChoose one option.

0.0 – 2.0

2.0 – 5.0

5.0 – 8.0

8.0 – 10.0

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GATE AE concept:load-factor PYQs

How to practice concept:load-factor

Question 33

Question 32

Question 60

Question 30

Question 25

Question 54

Question 40

Question 16