Great info. Moving the reference point for aggregate moment along the wing seems harder than just adding each lift x arm for each station outboard of the calculation point.
If I'm not mistaken for the bending moment could you use the method used to find the shear force, but replace the lift force with the shear force instead?
It's been a while so happy to be corrected but at 7min50sec shear from torsion is in the same radial direction through the cross section unless the tube isn't closed (has a slit down the length) then the shear stress is as shown in the diagram?
There isn't exactly a formula. You add an elliptical distribution (you can find these online) to a distribution that has the same shape as the planform of your wing. If you get Chris Heintz book "Flying on Your Own Wings" you will find the description on page 133.
Use a free 2D CAD software, draw an elliptical shape that has the same area as the lift. (Gross weight, times G load, multiplied by distance Center of Gravity is located in front of Aerodynamic Center, plus tail down-load). Draw the ellipse to represent the total load and lift with its area, make it the same span as the wing. Now, draw the wing planform sharing the same span and centerline. Now, scale the wing planform in 1D (vertically) until its area also equals the lift, same area as the ellipse. Now, draw small lines between the ellipse and scaled wing planform. It should be a relatively short distance. Now, place a point at the mid-point on each line. And connect them with a curve. The curve line should interpolate between the ellipse and the wing planform. This can be done on higher end CAD programs such as Rhino3D with the command "Tween two curves".
Great info. Moving the reference point for aggregate moment along the wing seems harder than just adding each lift x arm for each station outboard of the calculation point.
Congratulation, the quality of the exposed material is satisfying
can you elaborate the formula used for Schrenk Span Dist.
Very thorough explanation, thank you!
Very well explained. Good job.
If I'm not mistaken for the bending moment could you use the method used to find the shear force, but replace the lift force with the shear force instead?
How does one know the number of ribs for a given wing?
Can you make a new video that includes engine etc. loads on span?
It's been a while so happy to be corrected but at 7min50sec shear from torsion is in the same radial direction through the cross section unless the tube isn't closed (has a slit down the length) then the shear stress is as shown in the diagram?
Hi could you tell me what formula you used for the schrenk span dist please
There isn't exactly a formula. You add an elliptical distribution (you can find these online) to a distribution that has the same shape as the planform of your wing. If you get Chris Heintz book "Flying on Your Own Wings" you will find the description on page 133.
Use a free 2D CAD software, draw an elliptical shape that has the same area as the lift. (Gross weight, times G load, multiplied by distance Center of Gravity is located in front of Aerodynamic Center, plus tail down-load).
Draw the ellipse to represent the total load and lift with its area, make it the same span as the wing.
Now, draw the wing planform sharing the same span and centerline.
Now, scale the wing planform in 1D (vertically) until its area also equals the lift, same area as the ellipse.
Now, draw small lines between the ellipse and scaled wing planform. It should be a relatively short distance.
Now, place a point at the mid-point on each line. And connect them with a curve. The curve line should interpolate between the ellipse and the wing planform.
This can be done on higher end CAD programs such as Rhino3D with the command "Tween two curves".
Thanks a lot man
I think my comment got marked as spam again :)
👍
Terribly low volume audio.