Radicaldude1234
Well-Known Member
Hi guys,
I whipped up a configuration for my project here https://www.homebuiltairplanes.com/...aces-70-75-do-335-warning-large-pictures.html in XFLR5 to do some analysis.
The wing uses NACA 23000 series airfoils. I gave it an incidence angle of about 3 degrees to get the lift I need so that the aircraft pretty much cruises with a thrust-line angle of attack of 0 degrees. So in the picture below, 0 AOA corresponds to 3 degrees AOA for the wing chord line. Its at pretty much the static margin and moment slope angle I want to it to be at.
My problem right now is that I cannot get it to trim (Cm=0) at that point whilst keeping the static margin that I want. I'm trying to adjust the decalage but it still ends up short. The trim point will yield positive lift, but no enough for zero stick force. Am I doing something wrong, glossing over something, is it fine to begin with (just trim up; the moment is pretty small)?
Thanks in advance!
I whipped up a configuration for my project here https://www.homebuiltairplanes.com/...aces-70-75-do-335-warning-large-pictures.html in XFLR5 to do some analysis.
The wing uses NACA 23000 series airfoils. I gave it an incidence angle of about 3 degrees to get the lift I need so that the aircraft pretty much cruises with a thrust-line angle of attack of 0 degrees. So in the picture below, 0 AOA corresponds to 3 degrees AOA for the wing chord line. Its at pretty much the static margin and moment slope angle I want to it to be at.
My problem right now is that I cannot get it to trim (Cm=0) at that point whilst keeping the static margin that I want. I'm trying to adjust the decalage but it still ends up short. The trim point will yield positive lift, but no enough for zero stick force. Am I doing something wrong, glossing over something, is it fine to begin with (just trim up; the moment is pretty small)?
Thanks in advance!
