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Effect of Load Distribution

 Effect of Load Distribution

  • The effect of the position of the CG on the load imposed on an aircraft’s wing in fl ight is significant to climb and cruising performance.
  •  An aircraft with forward loading is “heavier” and consequently, slower than the same aircraft with the CG further aft.
  •  With forward loading,“nose-up” trim is required in most aircraft to maintain level
  • cruising fl ight.
  • Nose-up trim involves setting the tail surfaces to produce a greater down load on the aft portion of the fuselage, which adds to the wing loading and the total lift required from the wing if altitude is to be maintained.
  •  This requires a higher AOA of the wing, which results in more drag and, in turn, produces a higher stalling speed.
  • With aft loading and “nose-down” trim, the tail surfaces exert less down load, relieving the wing of that much wing loading and lift required to maintain altitude.
  •  The required AOA of the wing is less, so the drag is less, allowing for a faster cruise speed.
  •  Theoretically, a neutral load on the tail surfaces in cruising fl ight would produce the most effi cient overall performance and fastest cruising speed, but it would also result in instability.
  • Modern aircraft are designed to require a down load on the tail for stability and controllability.

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