A two-dimensional, diamond shaped supersonic airfoil has a total inclued angle of 15 degrees at its leading edge and its trailing edge. The maximum thickness of the airfoil is 0.5 ft. The airfoil is operating at a 5 degree angle of attack in a Mach 2.0 flow where the static pressure is 14.7 psia. Calculate the lift and drag on the airfoil in lbs force per foot of span, and determine the lift and drag coefficients for the airfoil.