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Ignoring thrust effects in a steady straight climb at a climb angle "gamma", the lift of an aeroplane with weight W is:
  • A
    W × (1-tan gamma)
  • B
    W × cos (gamma)
  • C
    W × (1-sin gamma)
  • D
    W ÷ cos (gamma)

Refer to figure.
Consider an aircraft in a straight steady climb along a straight flight path inclined at an angle (γ) to the horizontal. γ (gamma) is the symbol used for climb angle. The forces on the aircraft consist of Lift, normal to the flight path; Thrust and Drag, parallel to it; and Weight, parallel to the force of gravity.

Weight is resolved into two components: one opposite to Lift (W cos γ) and the other acting in the same direction as Drag (W sin γ), backwards along the flight path.
The requirements for equilibrium are: Thrust must equal the sum of Drag plus the backwards component of Weight; and Lift must equal its opposing component of Weight. For equilibrium at a greater angle of climb, the Lift required will be less, and the backwards component of Weight will be greater.

  • L = W cosγ
  • T = D + W sinγ

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