In flight mechanics, the angle of climb, denoted by γ (gamma), refers to the angle between the aircraft’s flight path and the horizontal plane while the aircraft is ascending or climbing. It is an essential parameter that describes the aircraft’s climb performance and how steeply it is ascending through the air.
The angle of climb is a measure of the aircraft’s vertical speed and is usually positive when the aircraft is climbing and negative when descending.
sin γ = (T – D) / W
This equation implies that the vertical component of the aircraft’s velocity (sin γ) is equal to the difference between thrust and drag (T – D), divided by the aircraft’s weight (W).
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