Question: 1 - Considering the wing section below, explain how there is lift at zero AOA 2 - Estimate the absolute pressure peak on the airfoil

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 1.225kgm???3, ambient pressure 101.34kPa,AOA=80. Use approximations on
the plot below.
1- Considering the wing section below, explain how there is lift

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