1- Considering the wing section below, explain how there is lift at zero AOA 2- Estimate the absolute pressure peak on the airfoil on an aircraft at landing speed EAS (Equivalent Air Speed) of 110 kn at sea level. Assume: air density 1.225 kg/m^3, ambient pressure 101.34 kPa, AOA = 8. Use approximations on the plot below. -6 CL = 4.81 -2 -4 =10 C = 4.26 =5 G=3.68 LI 74 0.2 0.4 0.6 0.8 1.0 x/c