Calculate the lift force generated by a NACA $1408$ airfoil with a chord of $1\mathrm{.}700$ m and a span of $11\mathrm{.}00$ m operating at $50\frac{m}{s}$ and an

angle of attack of $8$ degrees in air at a temperature of $20C$ and a pressure of $1$ atm $.$ The kinematic viscosity of air at $20C$ is $15\mathrm{.}11{10}^{-6}$

$\frac{m^2}{s^2}$

The lift force generated is

Ibf. $($Round the final answer to the nearest whole number.$)$