A Boeing 777-200LR loaded to 92% of its maximum take-off weight takes off from Dubai International Airport (24.4 m elevation) during an average day in July (34.5 OC) with a standard pressure day (101.3 kPa). Assume that the take off speed is 376 k ph. What is the minimum coefficient of lift needed at the point where the aircraft just lifts off the ground? A 777-200 has a maximum take-off weight is 347,452 kg and its wing area is 427.8 m2.
+33652 The lift coefficient is
$$C=\frac{L}{\frac{1}{2}\rho v^2 A}$$
Where L is the take-off weight (0.92*347452*9.81N), v is its take-off speed, A is its wing area and ρ is the air density (you didn't give that, so you'll need to look it up using the temperature and pressure).
+33652 The lift coefficient is
$$C=\frac{L}{\frac{1}{2}\rho v^2 A}$$
Where L is the take-off weight (0.92*347452*9.81N), v is its take-off speed, A is its wing area and ρ is the air density (you didn't give that, so you'll need to look it up using the temperature and pressure).
