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An aircraft is flying straight and level at 100 kts with a CL of 0.35. Its CLMAX is 1.22. Determine the maximum achievable load factor:
  • A
    2.68
  • B
    3.49
  • C
    4.22
  • D
    Insufficient information to make the calculation

The load factor (n) can be defined as the ratio of the actual lift of an aircraft to its weight (n = Lift / Weight). In straight and level flight, load factor equals 1.

The Lift (L) can be calculated using the following formula:

L = CL x Q x S
Where CL stands for coefficient of lift, Q is dynamic pressure and S represents wing area.

The question states that CL can be increased from 0.35 (present value) to 1.22 (CLMAX). Therefore, the maximum increase in lift is represented by a factor of: 1.22 / 0.35 = 3.49

  • Maximum achievable load factor = 1 x 3.49 = 3.49

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