Solve problems $3\mathrm{.}1$ in the textbook. Hand$-$written report is accepted. Submit in a pdf format.

The NACA $64-412$ is a cambered aerofoil with lift coefficient given by

$C_L=0\mathrm{.}11+0\mathrm{.}3$

where $$ is in degree units. What is the value of the constant pitching moment coefficient

about the aerodynamic centre? Estimate the position of the centre of pressure for the aerofoil

at an angle of attack of $5$ deg. State all assumptions made in answering this question.