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To calculate the lift force for the aircraft, we can use the lift equation:
Lift Force = 0.5 * Air Density * Velocity^2 * Wing Area * Lift Coefficient
First, we need to convert the velocity from km/h to m/s:
Velocity = 300 km/h = 300 * (1000 m / 3600 s) = 83.33 m/s
Now we can plug in the given values into the lift equation:
Lift Force = 0.5 * 0.92 kg/m^3 * (83.33 m/s)^2 * 29 m^2 * 0.81
Lift Force = 0.5 * 0.92 kg/m^3 * (6930.56 m^2/s^2) * 29 m^2 * 0.81
Lift Force = 0.5 * 0.92 * 6930.56 * 29 * 0.81
Lift Force ≈ 58679 N
Therefore, the lift force for this aircraft is approximately 58679 Newtons.