Timeline for Why is the numerically determined location of the center of pressure inaccurate near Cl = 0?
Current License: CC BY-SA 3.0
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| Mar 11, 2021 at 9:30 | comment | added | MikeB | So, would I be right in saying that the main problem here is that "centre of pressure" is an aggregate function, rather than a simple force? The wing itself is only providing lift "within itself" but that CoP also includes other components? | |
| Apr 23, 2016 at 18:33 | history | edited | Peter Kämpf | CC BY-SA 3.0 |
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| Apr 23, 2016 at 18:24 | comment | added | Peter Kämpf | @abcd The airfoil is creating both a moment (measured around the quarter chord point) and lift, and the moment is determined by camber, so it does not change with angle of attack (linear theory). When lift is very small, the lever arm to express the moment must become huge. | |
| Apr 23, 2016 at 10:46 | comment | added | abcd | Thank you for such a complete explanation. It still sounds me a bit counterintuitive. Mathematically I see it, when you weight the position "x" with the local lift coefficient (to calculate where the resultant is applied), since both "x" and "cl" can be negative, there may be some contribution that tends to set it out of the chord. Am I missing any important idea or simply there is no more on it? | |
| Apr 23, 2016 at 10:34 | history | edited | Peter Kämpf | CC BY-SA 3.0 |
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| Apr 23, 2016 at 10:25 | vote | accept | abcd | ||
| Apr 21, 2016 at 12:12 | comment | added | Peter Kämpf | @ROIMaison: I trust you understand German, so I recommend this page. | |
| Apr 21, 2016 at 7:49 | comment | added | ROIMaison | Could you elaborate a bit on the Birnbaum distribution? I tried to Google it, but I could only find references to unsteady flapping aerodynamics such as this one or should I ask this in a new question? | |
| Apr 21, 2016 at 6:47 | history | answered | Peter Kämpf | CC BY-SA 3.0 |