Over a certain range of air speeds, \(V\), the lift, \(F_{L}\), produced by a model of a complete aircraft in a wind tunnel depends on the air speed, air density, \(ho\), and a characteristic length (the wing base chord length, \(c=150 \mathrm{~mm}\) ). The following experimental data is obtained for air at standard atmospheric conditions:

Plot the lift versus speed curve. Generate and plot data for the lift produced by the prototype, which has a wing base chord length of \(5 \mathrm{~m}\), over a speed range of \(75 \mathrm{~m} / \mathrm{s}\) to \(250 \mathrm{~m} / \mathrm{s}\).

Transcribed Image Text:

V (m/s) 10 15 20 25 30 35 40 45 50 FL (N) 2.2 4.8 8.7 13.3 19.6 26.5 34.5 43.8 54