Wind tunnel testing of a high aspect ratio wing model

Abstract

There is much current interest in the development of High Aspect Ratio Wing (HARW) designs for improved aircraft performance. However, there are a lack of relevant data sets available to validate aeroelastic modelling approaches for highly flexible wings. The design and manufacture of a highly flexible 2.4m semi-span wing is described. A series of low speed wind tunnel tests were performed to generate displacement, acceleration, strain gauge, aerodynamic pressure and six component balance measurements for a range of airspeeds and wing root angles of attack. Numerous static and dynamic measurements were made. Preliminary results are shown for the static and dynamic, structural and aerodynamic behaviour over a range of different airspeeds and wing root angles of attack.