Q8. Use thin airfoil theory (slide 127) to calculate the lift and drag coefficient (show the contributions due to lift and thickness) on a biconvex airfoil as shown: The airfoil has a chord c = lm, a thickness to chord of 0.05 and is at 4 deg a. The Mach number is 2. The angle of the upper surface to the oncoming flow is given by: 2x 2x Ou = -a +0.1(1- and 01 = -a -0.1(1 - 24) (ans: CI=0.161, Cd=0.01895, Cl= Cdlift=0.01126 and Cdthickness=0.00769) a Q8. Use thin airfoil theory (slide 127) to calculate the lift and drag coefficient (show the contributions due to lift and thickness) on a biconvex airfoil as shown: The airfoil has a chord c = lm, a thickness to chord of 0.05 and is at 4 deg a. The Mach number is 2. The angle of the upper surface to the oncoming flow is given by: 2x 2x Ou = -a +0.1(1- and 01 = -a -0.1(1 - 24) (ans: CI=0.161, Cd=0.01895, Cl= Cdlift=0.01126 and Cdthickness=0.00769) a