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.

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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