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LaTeX Test Post Please Ignore

November 16, 2011

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.

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