Need help understanding a lift coefficient formula

AI Thread Summary
The discussion centers on the interpretation of the "relevant plan area" in the lift coefficient formula, specifically questioning its definition and implications. It is clarified that "relevant plan area" refers to the wing area and additional areas contributing to lift, such as the fuselage and other aerodynamic features. The formula indicates that as the area increases, the lift coefficient decreases, which aligns with the article's explanation. There is also a distinction made between the lift coefficient for the wing and the total lift coefficient for the entire airplane, particularly when considering downforce from stabilizers. Lastly, it is confirmed that the lift coefficient is dimensionless, contrary to the initial assumption of it having units of meters/second^2.
5P@N
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Please go to this Wikipedia article on Lift Coefficients, and behold the first formula. The last part of the equation has a "S" which is supposed to stand for "relevant plan area". Now, there was no explanation of what this "relevant plan area" is or means. I was guessing that it means the surface area of the airfoil, but this cannot be so, because as "S" is in the denominator of the formula, thus as the surface area increases, there is a diminished lift coefficient, and hence a diminished lift power (so my reasoning goes). I would write down the formula here, but for some reason Latex isn't working.

So: what is the "relevant plan area" referred to?
 
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"As relevant area is considered the wing area on profiles and the front area on vehicles."
 
For a given amount of lift, if you increase the area required to generate it the lift coefficient goes down. That's precisely what is written in the article with S in the denominator.
 
Relevant plan area refers to the area that significantly contributes to lift. On a normal airplane, S would just be wing area plus the area of the fuselage between the wing roots. But it also let's the formula apply to lifting bodies, airplanes with wide fuselages, chines, strakes, lifting stabilizer, etc.
 
It does. Thanks spamanon.
 
There is a lift coefficient for the wing, and a lift coefficient for the whole airplane (a.k.a. total lift coefficient). Total CL will be less than wing CL when the horizontal stabilizer generates a down force.
 
is anyone else having trouble with Latex? For some reason I don't have it anymore.
 
is a lift coefficient in units of meters/second^2?

Anyone?

I had performed a calculation of lifting force, and in order to be in Newtons, the lift coefficient would need to have these units...
 
  • #10
5P@N said:
is a lift coefficient in units of meters/second^2?

Anyone?

I had performed a calculation of lifting force, and in order to be in Newtons, the lift coefficient would need to have these units...
The definition I found is dimensionless.
 
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