Simplified Structural Analysis of a Wing (AerE 361)
Name:
Date Submitted:
Enter all data in SI units Input Cells Output Cells
Enter Wing Data:
Span (m) = 25
Root Chord (m) = 8
Last 2 NACA digits (4 digit) = 12
Enter Flight Data:
Density (kg/m^3) = 1.23
Velocity (m/s) = 600
Enter Lifting Line Data:
Coefficient A1 = 0.002
Coefficient A3 = 0.0002
Coefficient A5 = 0.0000002
Shear & Moment Calculation:
Shear at Clamp (output in Newtons) = 434717.883
Moment at Clamp (output in N.m) = 2444592.05
Beam Geometry Calculation at root (output):
Beam is assumed rectangular
Beam Height (output in m) = 0.96
Beam Width (output in m) = 0.32
g (AerE 361)
Stress and Factor of Safety Calculation
Yield Strength Aluminum (do not change in Pa)= 1.60E+08
Max. normal stress at root (output in Pa)= 49735353
Max. shear stress at root (output in Pa) = 2122646
Factor of Safety based on normal stress = 3.22E+00
Factor safety based on shear stress= 7.54E+01