Aeroelastic Scaling for Flexible High Aspect Ratio Wings

This paper provides an overview of the work conducted as part of the Cranfield BEAm Reduction and Dynamic Scaling (BeaRDS ) programme, which aims to develop a methodology for designing, manufacturing and testing of a dynamically scaled High Aspect Ratio (HAR) Wing inside Cranfield 8’x6’ wind tunnel. The aim of this paper is to develop a methodology that adopts scaling laws to allow experimental testing of a conceptual flexible-wing planform as part of the design process. Based on the Buckingham π theorem, a set of scaling laws are determined that enable the relationship between a full-scale and sub-scale model. The dynamically sub-scaled model is manufactured as a combination of spar, skin, and added mass representing the stiffness, aerodynamic profile, and aeroelastic behaviour respectively. The spar was manufactured as a cross-sectional shape using Aluminium material, while the skin was manufactured using PolyJet technology. Compromises due to the manufacturing process are outlined and lessons learned during the development of the sub-scaled model are highlighted.

[1]  Yiping Tang,et al.  Design and fabrication of stereolithography‐based aeroelastic wing models , 2011 .

[2]  Mayuresh J. Patil,et al.  Nonlinear Aeroelastic Scaled-Model Design , 2016 .

[3]  Sezsy Y. Yusuf,et al.  High Aspect Ratio Wing Design Using the Minimum Exergy Destruction Principle , 2019, AIAA Scitech 2019 Forum.

[4]  Edward M. Kraft After 40 Years Why Hasn't the Computer Replaced the Wind Tunnel? , 2010 .

[5]  Gaétan X. Dussart,et al.  Flexible high aspect ratio wing: Low cost experimental model and computational framework , 2018 .

[6]  Gaétan X. Dussart,et al.  Effect of wingtip morphing on the roll mode of a flexible aircraft , 2018 .

[7]  B. Moor,et al.  Subspace identification for linear systems , 1996 .

[8]  Mayuresh J. Patil,et al.  Nonlinear Aeroelastic-Scaled-Model Optimization Using Equivalent Static Loads , 2014 .

[9]  Mark French,et al.  Aeroelastic model design using parameter identification , 1996 .

[10]  W. J. Duncan Physical similarity and dimensional analysis : an elementary treatise , 1953 .

[11]  John J. Burken,et al.  Current and Future Research in Active Control of Lightweight, Flexible Structures Using the X-56 Aircraft , 2014 .

[12]  Afzal Suleman,et al.  Aeroelastic Scaling of a Joined Wing for Nonlinear Geometric Stiffness , 2012 .

[13]  Stuart P. Andrews,et al.  Modelling and simulation of flexible aircraft : handling qualities with active load control , 2011 .

[14]  Christopher K. Droney,et al.  Subsonic Ultra Green Aircraft Research Phase II: N+4 Advanced Concept Development , 2012 .

[15]  Fernando Lau,et al.  Nonlinear aeroelastic scaling of high aspect-ratio wings , 2017 .

[16]  Jennifer Heeg,et al.  Wind Tunnel to Atmospheric Mapping for Static Aeroelastic Scaling , 2004 .

[17]  Carlos E. S. Cesnik,et al.  Geometrically Nonlinear Aeroelastic Scaling for Very Flexible Aircraft , 2013 .

[18]  E. Torenbeek,et al.  Development and application of a comprehensive, design-sensitive weight prediction method for wing structures of transport category aircraft , 1992 .