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eng.wing-bending-stress-beam Calculator
Calculates wing bending stress at the root section from lift distribution and structural geometry using simple beam theory. Wing root bending moment at 2.5g manoeuvre load is the critical sizing case — the semi-monocoque box spar resists this bending.
Inputs
L Span M
Distance between supports (m). Longer spans experience larger bending moments — structural adequacy must be rechecked.
W N M
Applied force or weight (N or kN). Divide into dead load (permanent) and live load (variable — people, wind, etc.).
I M4
Two-dimensional surface extent (m²). For complex shapes, break into simpler sub-shapes and sum.
C M
Separation between two points or total path length. Check that units are consistent throughout the calculation.
Results
root bending moment M (kN·m)
Internal tendency to bend the beam at a given cross-section (N·m). Maximum bending moment governs beam sizing — the beam must resist bending at the critical section.
max bending stress σ (MPa)
Internal force per unit area (Pa or MPa). Must stay below yield strength in service. Beyond yield: permanent deformation. Beyond tensile strength: fracture.
root shear force V (kN)
Internal force acting parallel to the cross-section (N). Governs design of short, heavily loaded beams and connections. Maximum shear is usually at the supports.
tip deflection (Al, E=70 GPa, m)
Maximum lateral displacement of the beam under load. Codes typically limit to L/360 for floors (to avoid cracking finishes) or L/240 for roofs. Excessive deflection signals the beam is undersized.
M_root = wL²/2
Reference formula or conversion factor shown for context.
σ = Mc/I
Reference formula or conversion factor shown for context.