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. and lift coefficient is 0.81 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 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.