On determination of aerodynamic properties of morphing wing by numerical simulations

The increasing demand for more efficient and eco-smart aviation necessitates the exploration of novel aerodynamic control mechanisms. This study explores a preliminary numerical investigation of a wing concept with partial morphing in the chord-wise direction. The motivation behind this design is use wing morphing for flight control and maneuvering, which could lead to improved aerodynamic efficiency and reduced flight costs. The current effort is dedicated to establishing a robust numerical framework and gaining preliminary insights into the aerodynamic characteristics of relevant airfoil profiles. At this stage, the research focuses on adapting numerical models and conducting two-dimensional static aerodynamic simulations to evaluate the feasibility of the concept. Two airfoils, LS-0417 and FX 66-S-196 V1, have been selected as baseline profiles for this study with the LS 0417 profile serving as the primary default. To establish the reliability of the numerical approach, an initial validation is conducted by comparing computational results of the hinge moment coefficient for the LS-0417 airfoil with a 20% chord aileron at a Reynolds number of 2.2 million against published experimental data from Wentz et al. The results demonstrated good agreement, confirming the validity of the simulation setup. Building upon this validated setup, further simulations are carried out for both the LS-0417 and FX 66-S-196 V1 profiles at a Reynolds number of 0.833 million. This investigation includes the analysis of key aerodynamic characteristics such as lift-to-drag ratios, as well as the distribution of pressure and skin friction coefficients. These numerical simulations provide crucial insights into their aerodynamic performance under relevant flow conditions. By establishing a reliable numerical framework, this research aims to identify the aerodynamic advantages and potential limitations of the morphing concept. The insights gained from these studies will contribute to the future steps including wind tunnel testing to validate the numerical findings and assess the performance of a manufactured wing.