Design of a Wing Structure for a Single Turboprop Normal Category Aircraft
This paper presents the wing design and structural analysis of a single turboprop
aircraft with a maximum take-off weight of 2,200 lbs. The aircraft’s wing
structure is a conventional mid-wing configuration of a twisting trapezoidal
planform with an aspect ratio of 0.6. The analysis involved determining the loads
acting on the wing structure. That is, the aircraft’s flight envelope and the wing’s
critical loading condition are according to Title 14 Code of Federal Regulations
Part 23 (14 CFR Part 23). The wing CAD model, composed of the aircraft wing
components of the spar, ribs, and skins, including its layout, was developed and
analyzed based on available 7075T6 Aluminum sheets using the SolidWorks
software. The results for the wing’s critical loading condition showed that the
wing tip displacement was less than 5% of the half-wingspan with a margin of
safety of 0.5 and a mass of 117.97 lbs which was less than the expected mass of 132
Wing Structural Design
Finite Element Analysis
Normal Category Aircraft
14 CFR Part 23
Single Turboprop Aircraft
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