- 32,835
- 38,108
Also the area is still incorrect.Updated the area and hollowness and added a new end for the laminated carbon
Gonna add 2 new ends assuming that half the wings is steel now
Actual area affected would be width * thickness. Since it's the area connecting it. It'd be like a thin, hollow rectangle, not unlike the opening in thin rectangular medicine boxes. Think of it like the front face of the wing when detached.
0.4694 * 0.069= 0.0323886 m^2. Times 0.05 for 95% hollowness is 0.00161943 m^2. Per wing.
Times 2 because two wings is 0.00323886 m^2.
Laminated (1.6 GPa or 1.6e+9 Pa): 0.00323886 * 1.6e+9 GPa= 5182176 N or 528434.8886 kgf (Class K)
Another end (3.5 GPa or 3.5e+9 Pa): 0.00323886 * 3.5e+9 GPa= 11336010 N or 1155951.3188 kgf (Class M)
I saw some 2.2 and 2.7 GPa ends online as well. Should I add those in?