Development and testing of a variable camber morphing wing mechanism

Evans, Cerys; Harmer, Morgan; Marks, Oliver; Tiley, Stephen; Willis, Tom; Bouferrouk, Abdessalem; Yao, Yufeng

Abstract

The aim of this study was to develop, build and test a morphing wing design in a low-speed wind tunnel to demonstrate its viability as a practical morphing mechanism. The original concept this study is based upon is so-called the Direct Control Airfoil Geometry (DCAG) which has not previously been manufactured or physically tested. The concept was modified to apply to a NACA 0012 wing trailing edge flap configuration, scaled to 1m chord and 0.33m span due to design constraints for manufacture, assembly and wind tunnel testing. A silicone rubber wing skin was used which provided certain morphing capability, although it did not fully adhere to the proposed flap geometry. The study demonstrated that the DCGA concept physically works as a feasible trailing edge morphing mechanism and can resist aerodynamic and structural loadings. The findings so far are promising for future integration of the DCAG concept on full-scale aircraft.

Citation

Evans, C., Harmer, M., Marks, O., Tiley, S., Willis, T., Bouferrouk, A., & Yao, Y. (2016, May). Development and testing of a variable camber morphing wing mechanism. Paper presented at International Symposium of Sustainable Aviation, Istanbul, Turkey

• Presentation Conference Type: Conference Paper (unpublished)
• Conference Name: International Symposium of Sustainable Aviation
• Conference Location: Istanbul, Turkey
• Start Date: May 29, 2016
• End Date: Jun 1, 2016
• Acceptance Date: May 5, 2016
• Publication Date: Jan 1, 2016
• Deposit Date: Sep 5, 2016
• Publicly Available Date: Sep 6, 2016
• Peer Reviewed: Peer Reviewed
• Keywords: aviation
• Public URL: https://uwe-repository.worktribe.com/output/918601
• Additional Information: Title of Conference or Conference Proceedings : International Symposium of Sustainable Aviation (ISSA)