1. The problem statement, all variables and given/known data Missile Calculate the drag force on a missile 48 cm in diameter cruising with a speed of 270 m/s at low altitude, where the density of air is 1.2 kg/m3. Assume C = 0.75. 2. Relevant equations Fd = -1/2p(v^2)CA 3. The attempt at a solution -1/2(1.2)(270^2)(0.75(0.48) = -15746.4 what am i doing wrong?