$q_\infty=\frac{1}{2} \rho V_\infty^{2}$

$L=q_\infty C_L S_{ref}$

$L=\frac{1}{2} \rho C_L S_{ref} V_\infty^{2}$

$F=m a$

$a=\frac{v^{2}}{r}$

If you got here by mistake, this was just a test for LaTeX which I used later in my article on Aerodynamic Coefficients: Lift.