Problem $1$: Consider an infinite wing with a NACA $1412$ airfoil section and a chord length of

$1\mathrm{.}881$ m $.$ The wind is at an angle of attack of $-9\mathrm{.}615$ degrees in an airflow velocity of $51\mathrm{.}807$

$\frac{m}{s}$ at standard sea$-$level conditions. No simulated flaps are deployed, and the surfaces are

smooth. Calculate the lift produced by the airfoil section.

Express your answer in N up to $3$ decimal places.

Note: Use the NACA $1412$ plots in the appendix of the textbook or the transcribed excel data

to obtain the needed coefficients based on the closest available Reynolds number.

Calculate the lift produced by the airfoil section

Enter the lift coefficient cL:

: Enter the dynamic pressure qinf in kg$/($ms$2)$: