- #1

billy92

- 12

- 0

I understand the theory behind the lift force produced by different pressures above and below the wing. However, i need to use equations which i can show how to derive in the report.

I have found the following equation [itex]\frac{1}{2}ρv^{2}AC_{L}[/itex] but i am not sure how to derive this equation.

Thanks