The wing loading on an airplane is defined as the aircraft weight divided by the wing area. An airplane with a wing loading of 2000 N/m² has the aerodynamic characteristics given by Fig. 11.25. Under cruise conditions the lift coefficient is 0.3. If the wing area is 10 m², find the drag force.

In Fig. 11.25

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1.20 FIGURE 11.25 Coefficients of lift and drag for a wing with an aspect ratio of 5. [After Prandti (23).] 1.00 0.20 0.80 0.16 CL 0.60 0.12 Cp 0.40 0.08 Cpi 0.20 0.04 4 12 16 Angle of attack, a, degrees