Aerospace Engineering > GATE 2021 > Aircraft Maneuvering
For a conventional fixed-wing aircraft in a 360° inverted vertical loop maneuver, what is the load factor (n) at the topmost point of the loop? Assume the flight to be steady at the topmost point.
A
n = 1
B
n < 1
C
n = -1
D
n > -1

Correct : d

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Related Topics

fixed wing aircraft loop maneuver GATE Aerospace Engineering 2021 load factor inverted loop aerospace engineering gate flight dynamics loop GATE 2021 question 30 aircraft stability inverted loop load factor inverted loop solution

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