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Originally Posted by ryan1234
There seems to be a misconception that an increase in a specifc C/L is a total increase in lift... this is not true... total lift can only be increased when C/Lmax is increased
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WHAT!?!?!? Absolutely 100 percent wrong sir. Cl max is the limiting factor for a wings ability to create lift. Meaning above Cl max the wing is stalled, Cl max has absolutely no bearing on the lift a wing is creating at any given point in time. Cl max only means the limit at which the wing can produce lift before being stalled, in most lift formula it is found by (2 pi AOA) just to keep things simple.
Also, increase in Cl is unquestionably an increase in total lift. Lift = velocity squared * wing area * air density *
coefficient of lift. How can Cl go up, a value in the lift formula increase, but lift not increase?
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this could alter what is "felt".
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An aircraft does not feel, no more than you are effected by the wind outside the bus on the ride to work. (not saying you take a bus)
If Cl goes up, lift goes up period. period.
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basically you encounter higher lift conditions at a lower AoA
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You agree with us, you just don't realize it. Look at a situation given this above statement: wings AOA 10 degrees producing 2000 lift to offset 2000 pounds. Now you said for any given AOA there is an increase (this increase is because of Cl) in lift when in ground effect. Leave the aircraft at 10 degrees now and put it in ground effect, by your statement lift has now gone up say 2100 pounds and you would balloon back out of ground effect if you left the AOA at 10 degrees.
So lift did go up didn't it? You reduced AOA to keep lift from going up in your example, but that doesn't mean it didn't go up. So, you see you agree, you just have some misconceptions in there.
