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.?
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.