An aircraft with a wing area of 29 m flies with a velocity of 300 km/h, at an altitude where the air density is 0.92 kg/m^3. Its angle of attack is 7. The figure below shows the lift and drag coefficients for the wings of this aircraft. Calculate the lift force for this aircraft.?

Answer 1

To calculate the lift force for the aircraft, we need to use the lift equation:

Lift Force = 0.5 * air density * velocity^2 * wing area * lift coefficient

First, let's convert the velocity from km/h to m/s:

300 km/h * (1/3.6) m/s = 83.33 m/s

Now, we can calculate the lift force using the given values:

Lift Force = 0.5 * 0.92 kg/m^3 * (83.33 m/s)^2 * 29 m^2 * lift coefficient

Since the lift coefficient is not given, we can't calculate the lift force precisely.