Consider an NACA 2412 airfoil with chord of 1.5 m at an angle of attack of 4°. For a free-stream velocity of 30 m/s at standard sea-level conditions, calculate the lift and drag per unit span.
Consider an NACA 2412 airfoil with chord of 1.5 m at an angle of attack of 4°. For a free-stream velocity of 30 m/s at standard sea-level conditions, calculate the lift and drag per unit span.
For NACA 2412 angle of attack at 4°, coefficient of lift is nearly 0.65 and coefficient of drag is nearly 0.04.
Lift per unit span is
\[{L}’ = \frac{1}{2}\rho_{\infty}V^{2}Cc_{l}\]
\[{L}’ = \frac{1}{2}\left ( 1.225 \right )\left ( 30 \right )^{2}1.5\left ( 0.65 \right ) = 537.5N/m\]
Drag per unit span is
\[{D}’ = \frac{1}{2}\rho_{\infty}V^{2}Cc_{d}\]
\[{D}’ = \frac{1}{2}\left ( 1.225 \right )\left ( 30 \right )^{2}1.5\left ( 0.04 \right ) = 33.075N/m\]
