The Concorde, the now retired supersonic passenger plane, was able to cruise at Mach 2.04 (2500 km/h) at 18.4 km above sea level. At this altitude, the density of air is ~ 0.13 kg/m3. Assume that the mass of the Concorde was 111,000 kg and, when cruising, all upward forces came from lift. What was the lift coefficient of the Concorde when cruising taking the area of the wings to be 358.25 m2?