The Suction Panel - xHLFC and Structural Solution for Energy Efficient Aviation

Wiedemann, Martin; Badrya, Camil; Prasannakumar, Adarsh; Lobitz, Lennart; Traub, Hendrik; Heimbs, Sebastian; Hühne, Christian; Saemann, Philipp G.; Buelow, Christian; Scheffler, Sven; Brod, Martin; Tariq, Muzzamil

doi:10.2514/6.2022-0007

Cited by 2 publications

(1 citation statement)

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“…Its task is to unload the suction panel and provide the stiffness needed to prevent the suction panel from experiencing excessive bending loads. Benefits from thin-ply laminates have been investigated in the scope of this research as an option to compensate for the additional mass associated with the suction panel integration [13]. However, this is not taken into account in this paper.…”

Section: Introductionmentioning

confidence: 99%

Aircraft Wing Design for Extended Hybrid Laminar Flow Control

Lobitz,

Traub,

Overbeck

et al. 2023

Aerospace

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Laminar flow offers significant potential for increasing the energy-efficiency of future transport aircraft. The German Cluster of Excellence SE2A is developing a new approach for hybrid laminar flow control. The concept aims to maintain laminar flow up to 80% of the chord length by integrating suction panels at the rear part of the wing, which consist of a thin suction skin and a supporting core structure. This study examines effects of various suction panel configurations on wing mass and load transfer for an all-electric short-range aircraft. Suction panel material, as well as thickness and relative density of the suction panel core are modified in meaningful boundaries. Suction panels made from Ti6Al4V offer the most robust design resulting in a significant increase in wing mass. For the studied configurations, they represent up to 33.8% of the mass of the wingbox. In contrast, panels made from Nylon11CF or PU1000 do not significantly increase the wing mass. However, the use of these materials raises questions about their robustness under operational conditions. The results demonstrate that the choice of material strongly influences the load path within the wing structure. Ti6Al4V suction panels provide sufficient mechanical properties to significantly contribute to load transfer and buckling stiffness. Locally, the share of load transfer attributed to the suction panel exceeds 50%. In contrast, compliant materials such as Nylon11CF or PU1000 are inherently decoupled from load transfer. Unlike the thickness of the suction skin, the relative density of the core structure strongly affects the wrinkling stiffness. However, wrinkling failure did not appear critical for the examined suction panel configurations. In the present study, the mechanical properties of Ti6Al4V cannot fully be exploited. Therefore, compliant suction panels made from Nylon11CF are preferred in order to achieve a lightweight solution, provided that they meet operational requirements.

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Section: Introductionmentioning

confidence: 99%