Discussion
An aircraft of weight \(50\) kN flies level with a wing area of \(25\) m squared at a dynamic pressure of \(4000\) Pa. The required lift coefficient is
Answer: B
Correct answer: 0.5
In level flight lift equals weight, so \[ C_L = \frac{W}{qS} = \frac{50\,000}{4000 \times 25} = \frac{50\,000}{100\,000} = 0.5. \] The lift coefficient is therefore not a fixed property of the wing but whatever the flight condition demands: fly slower and \( q \) falls, so \( C_L \) must rise, until it reaches the maximum the section can supply and the aircraft stalls.
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