Aerowerx
Well-Known Member
I don't know why I had so much trouble figuring this out. Maybe I'm just getting too old.
I am trying to create an Excel spreadsheet to do flying wing geometry calculations, which I can then enter into XFLR5. Now, XFLR5 requires that you enter the Leading Edge offset from the reference datum and chord for each wing station. It then calculates the sweep angle based on the quarter chord point. "Everybody else" starts with the sweep angle and chord.
It took me a while, but I finally figured out the formula at about 2am last night, and I thought someone else may need this. It was created for a swept tapered wing, but will work for any wing shape, even
forward sweep.
Rc is the root chord
Lc is the local chord at the wing station
A is the sweep angle
L is the wing station
O is the offset from the datum. It is assumes that the datum is at X=0.0
O=0.25*Rc-0.25*Lc+L*Tan(A)
I am trying to create an Excel spreadsheet to do flying wing geometry calculations, which I can then enter into XFLR5. Now, XFLR5 requires that you enter the Leading Edge offset from the reference datum and chord for each wing station. It then calculates the sweep angle based on the quarter chord point. "Everybody else" starts with the sweep angle and chord.
It took me a while, but I finally figured out the formula at about 2am last night, and I thought someone else may need this. It was created for a swept tapered wing, but will work for any wing shape, even
forward sweep.Rc is the root chord
Lc is the local chord at the wing station
A is the sweep angle
L is the wing station
O is the offset from the datum. It is assumes that the datum is at X=0.0
O=0.25*Rc-0.25*Lc+L*Tan(A)
