Wing and blade aerodynaimc center
Wing and blade aerodynaimc center
(OP)
Hello everyone,
Now i am trying to model wind turbine blade using solidworks.
I have the airfoil coordinates at each section of the blade, but the coordinates are distance per chord (x/c,y/c) so i have to scale it using the calculated chord.
When i scale it with respect to the origin - which is at the leading edge - the position of the aerodynamic center for each section is changed with respect to others.
Is the aerodynamic center should be along the same line??
Is this correct or should i do it another way?
Thanks in advance.
Now i am trying to model wind turbine blade using solidworks.
I have the airfoil coordinates at each section of the blade, but the coordinates are distance per chord (x/c,y/c) so i have to scale it using the calculated chord.
When i scale it with respect to the origin - which is at the leading edge - the position of the aerodynamic center for each section is changed with respect to others.
Is the aerodynamic center should be along the same line??
Is this correct or should i do it another way?
Thanks in advance.





RE: Wing and blade aerodynaimc center
Try to remember, though, that the wind turbine blade will be rotating at many many RPM, (depending on its size). If the center of mass of each cross-section meanders like the aerodynamic center line, then it will not be well aligned radially with the axis of rotation either. An induced lead/lag load will be present, which may be insignificant, or cause problems, depending on the size of the turbine and the materials you use.
STF
RE: Wing and blade aerodynaimc center
the chords are non-dimensional (x/c, y/c), the datum for the axes is (0,0).
why do you care particularly about the ac ? (it is "only" the point where Cm is zero)
RE: Wing and blade aerodynaimc center
Taking in consideration that it is only one section and we must have N number of sections, so the other sections should have the same reference point for consistency.
i tried to draw the blade using each AC of the airfoil at each section (c/4) and it looks like this
The project i used as a guide looks like this
RE: Wing and blade aerodynaimc center
But it still different from the original one and i don't have another reference to compare with
RE: Wing and blade aerodynaimc center
the aerodynamic centre moves as the conditions (certainly AoA, maybe airspeed) change ... it is he point abot which aerodynamic moments are zero, lok at the plot of Cm, it isn't constant.
the 1/4 chord point might be a logical point to overplot airfoils (sections along your blade) ... it is the reference point for aerodynamic coefficients.
the axis (CL) of the blade mounting would obviously be releent to your application ... maybe a better choice.
it's simple enough to transform the co-ordinates of your airfoil to move the origin to another point, yes?
RE: Wing and blade aerodynaimc center