Calculate Lift Coefficient

[JABBARA]

To get an exact value you need detailed aerodynamic information that is almost never published

I totally agree


Hi Wizofoz

Lift is the sum of all vertical forces on the aircraft, and in cruise is equal to weight. Yes, the wing has to produce extra lift to over come the downforce of the tail

I agree, I mean the same.

some models actually have a lifting tail

This is mostly correct for naturally designed unstable fighter jets (but to be controlled only by FBW), not for Transport Category Airplane

Co-efficient of lift refers to the whole airframe, not just the wing

, I agree, I mean the same

Of course I agree with the equation "

so entering values to the equations L=C 1/2 RHO V^2,

but "S" is missing.

But my knowledge of Flight Mechanics tells me here: L is always bigger than W. As below.




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At the end, I am not an expert, I may be missing something. if correct me I will be happy.

Thanks