Discussion
An aircraft's drag coefficient is \( 0.025 \) on a wing area of \( 30 \) m\( ^2 \). At \( 80 \) m/s its drag is nearest to
Answer: B
The dynamic pressure is \( 0.5 \times 1.225 \times 80^2 = 3920 \) Pa, so the drag is \( 0.025 \times 3920 \times 30 = 2940 \) N. In steady level flight the thrust required is exactly this, so the power needed is the drag times the speed, about 235 kW.
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