Keywords
Cantilever Wing
Static Analysis
Buckling Analysis
How to Cite
Abstract
The current research presents a benchmarking analysis between the cantilever and braced wing configurations across a range of aspect ratios. The structural efficiency of these two configurations is bench-marked in order to provide recommendations for the use of wing braces in different scenarios. The reference aircraft was the Cessna 408 Skycourier. The study encompasses five different aspect ratios, ranging from 9.8 to 13.8. The two configurations have been compared in terms of their performance using both linear static analysis and buckling analysis. The analyses addressed factors such as stress distribution, peak stress, and critical buckling loads. Additionally, the brace connection angle impact on the braced wing configuration has been studied. The results have corroborated the bibliography in the way they have shown that the braced wing configuration is structurally more efficient than the cantilevered one. The results indicate a structural mass saving on the wing of about 39%. These savings could mean a 25% fuel mass saving for the same mission or an approximate increase in 25% of the aircraft payload.
References
Bai, X., Liu, L., Zhang, S., Song, C., & Guo, F. (2024). Assembly error space dimensional chain construction and assembly process optimization method for segmented wing structure. In Proceedings of the 6th China Aero- nautical Science and Technology Conference (CASTC 2023) (pp. 382–393). Springer. https://doi.org/10.1007/ 978-981-99-8867-9_36
Cessna SkyCourier. (n.d.). Cessna.txtav.com. https://cessna.txtav.com/en/lp/skycourier-splash-lp
Chiozzotto, Gabriel. (2016). Wing weight estimation in conceptual design: a method for strut-braced wings considering static aeroelastic effects. CEAS Aeronautical Journal. 7. doi:10.1007/s13272-016-0204-5
DE HAVILLAND CANADA DHC-6 | SKYbrary Aviation Safety. (n.d.). Skybrary.aero. https://skybrary.aero/ aircraft/dhc6
Dornier DO 228-101 D-CODE. (2017). DLR.de. https://www.dlr.de/en/research-and-transfer/research-infrastructure/research-aircraft-fleet/dornier-do-228-101-d-code
European Union Aviation Safety Agency (EASA). (n.d.). CS-23 normal, utility, aerobatic and commuter aeroplanes. https://www.easa.europa.eu/en/document-library/certification-specifications/group/cs-23-normal-utility-aerobatic-and-commuter-aeroplanes
Gudmundsson, S. (2022). General aviation aircraft design: Applied methods and procedures (2nd ed.). Butterworth- -Heinemann.
Gur, O., Bhatia, M., Schetz, J., Mason, W., Kapania, R., & Mavris, D. (2010). Design Optimization of a Truss- -Braced-Wing Transonic Transport Aircraft. Journal of Aircraft, 47, 1907-1917. https://doi.org/10.2514/1.47546.
Jet fuel. (2025, September 7). In Wikipedia. Retrieved September 25, 2025, from https://en.wikipedia.org/wiki/Jet_fuel
Jones, B., Nagy, P., Minisci, E., & Fossati, M. (2023). A geometric sensitivity study for the aerodynamics of a strut-braced airframe. Aerospace Science and Technology. https://doi.org/10.1016/j.ast.2023.108638.
Judt, D., Lawson, C., & Lockett, H. (2019). Experimental investigation into aircraft system manual assembly per- formance under varying structural component orientations. Proceedings of the Institution of Mechanical Engineers, Part B: Journal of Engineering Manufacture, 234(4), 840–855. https://doi.org/10.1177/0954405419883047
LET L-410/420 | SKYbrary Aviation Safety. (2021). Skybrary.aero. https://skybrary.aero/aircraft/l410
Liu, L., & Yu, X. (2020). A Study on Aerodynamic Interference for Truss Braced Wing Configuration, 129-152. https://doi.org/10.1007/978-981-33-6060-0_10.
Lynch, K. (2019, May 19). Textron’s skycourier takes shape. AIN Online. Retrieved September 25, 2025, from https://www.ainonline.com/aviation-news/business-aviation/2019-05-19/textrons-skycourier-takes-shape
Lovero, F., Biggi, G., Lombardi, S., Costa, M., Amore, V., & Cestino, E. (n.d.). EXPERIMENTAL VALIDATION OF THE DYNAMIC FINITE ELEMENT MODEL OF A 1:8 SCALE SEAPLANE USING A LASER DOPPLER VIBROMETER (LDV). Retrieved October 2, 2025, from https://www.icas.org/icas_archive/icas2024/data/papers/icas2024_0730_paper.pdf
Lung, S. (2009). Ground vibration test and model updating of the Aerostructures Test Wing (ATW2). NASA Technical Report. https://ntrs.nasa.gov/api/citations/20090019136/downloads/20090019136.pdf
M28 Technical data PZL Mielec. (2024). Pzlmielec.pl. https://pzlmielec.pl/en/offer/m28-05/technical-data
Nadezhda Zaitseva, Sergey Lupuleac, & Shinder, J. (2024). Initial gap modeling for wing assembly analysis. Aerospace Systems. https://doi.org/10.1007/s42401-024-00302-4
Pawlowski, F. W. (1917). Evolution of airplane wing-trussing. Journal of the Society of Automotive Engineers, 355–359. https://www.jstor.org/stable/44716165
Psyk, V., Linnemann, M., Henkel, M., Kräusel, V., & Dix, M. (2024). Joint design for strut connections in airplane structures produced by electromagnetic forming. In Proceedings of the 14th International Conference on the Technology of Plasticity – ICTP 2023 (pp. 149–156). Springer.
PT Dirgantara Indonesia. (2025). N219. https://www.indonesianaerospace.com/en/portfolio/aircraft/fixed_wing/detail/11/n219-
Roskam, J. (1999). Airplane design: Part III – Layout design of cockpit, fuselage, wing and empennage: Cutaways and inboard profiles. DARcorporation.
Taflan, M., Smith, H., & Loughlan, J. (2023). Parametric Analysis for Structural Design and Weight Estimation of Cantilever and Strut-Braced Wing-Boxes. AIAA SCITECH 2023 Forum. https://doi.org/10.2514/6.2023-1554.
Vale, P. (2024). Aircraft wing structure benchmark: cantilever vs. braced wing configurations (Dissertação de mestrado, Universidade do Minho). RepositóriUM. https://repositorium.uminho.pt/entities/publication/13f68aa2-8d6c-4aa6-8fdd-4cfcade0dd9c
Wang, Q., Dou, Y., Li, J., Ke, Y., Keogh, P., & Maropoulos, P. G. (2017). An assembly gap control method based on posture alignment of wing panels in aircraft assembly. Assembly Automation, 37(4), 422–433. https://doi.org/10.1108/aa-04-2016-031
Zhang, W., An, L., Chen, Y., Xiong, Y., & Liao, Y. (2021). Optimisation for clamping force of aircraft composite structure assembly considering form defects and part deformations. Advances in Mechanical Engineering, 13(4). https://doi.org/10.1177/1687814021995703