Problem 3. Linear Cp Distribution A thin airfoil is measured to have the following linear Cp distributions on its upper and lower surfaces at some small angle of attack a. -1.0 (1 - x/c) == = 0.5 (1x/c) -Cp\ C'pl X 3.1) Determine the lift coefficient c. You may assume that a < < 1. 3.2) Determine the moment coefficient Cmc/4 about the quarter-chord location x = = c/4. 3.3) Determine center of pressure location xcp.