Over the years there has been a dramatic increase in the flight speed \((U)\), altitude \((h)\), weight \((\mathcal{W})\), and wing loading ( \(W / A=\) weight divided by wing area) of aircraft. Use the data given in the table below to determine the lift coefficient for each of the aircraft listed.

Aircraft Year W, lb U, mph W/A, lb/ft2 h, ft Wright Flyer 1903 750 35 1.5 0 Douglas DC-3 1935 25,000 180 25.0 10,000 Douglas DC-6 Boeing 747 1947 105,000 315 72.0 15,000 1970 800,000 570 150.0 30,000