Static aeroelastic analysis of high aspect ratio flexible wing

The purpose of this thesis is to analyze of high aspect ratio flexible wing based upon static aeroelasticity. This problem is solved using various mesh concentration. So lift coeffient is checked under various mesh quality. The selected mesh is used to analyze of three turbulence models under various angle of attack. The selected turbulence model is k-w-SST for this study. This turbulence model is found to be more suitable for the utilized velocity and Reynolds number. Furthermore, drag and lift coeffients and their ratios are determined for the different aspect ratios, attack angles and dihedral angles (cases). In this study, zero dihedral angle is selected as a starting point and the same load is applied successively four times. Each load effect is defined as a case (0,1,2,3). Some useful results have been obtained from these analyses and in addition, due to obtained results, Aspect Ratio 9 is recommended to use due to its lower solution time and higher natural frequency. All these obtained results will give useful and beneficial contributions for unmanned aerial vehicle (UAV), training propeller aircraft and glider designers.