However, it was only with the recent advancements with the smart composite materials and structural designs that wing morphing in the modern flight speeds have become technologically viable. The wing morphing concept’s origins could be traced back to the Wright Brothers’ wing warping design to produce a rolling motion by twisting the wing in flight. Hence, the morphing wing design may deliver superior aerodynamic performance. In contrast, modern morphing wings maintain a smooth variation along the wing surface, which removes the effects of discontinuity in the geometry. However, the discontinuity in wing geometry introduced by those mechanisms typically leads to non-uniform aerodynamic profiles and increased drag. In conventional aircraft, lift enhancing mechanisms such as the flaps and slats are incorporated into the wings to increase the aerodynamic performance. An increase in aerodynamic performance leads to higher fuel efficiency, range, and endurance than conventional in-flight actuators, such as flaps and slats currently used in commercial aircraft. The ability to modify a wing’s geometry during flight allows the aircraft to achieve optimal aerodynamic performance at every stage of its mission profile. Morphing wing actuation technology is a research area of importance due to its capability to increase aircraft performance and maneuverability by adapting the wing shape to the various flight conditions. The study demonstrates that morphing wings can achieve significant aerodynamic performance gains through active actuation of hinge point location and control deflection to suit the flight regimes encountered through a mission profile. The results also indicated that the morphing wing shape optimization should start from lower values of control deflection and hinge location as an initial design approach. The results showed that a higher Reynolds number leads to better aerodynamic performance while the control deflection and hinge location needs to be optimized for a given flight condition. The CFD simulations are performed using the three- dimensional (3D) Reynolds-Average Navier-Stokes (RANS) equations with the k – ω Shear Stress Transport (SST) turbulence model. This research was conducted numerically through Computational Fluid Dynamics (CFD) simulations. Control deflection for the trailing edge, hinge location, Reynolds number, and angle of attack were parameterized to investigate trends.
Following the authors' previous study, an elliptical curve was used as the morphing model for the spanwise trailing edge deflection. The morphing wing presented considers a NACA 0012 airfoil with a rigid portion at the leading edge and a continuously conforming trailing edge flap. Atlikus analize nustatyta, kad tos pacios stygos ilgio asimetrinio profilio mente generuoja didesni sukimo momenta, tuo paciu ir galia, negu simetrinio profilio mente.In this research, the morphing wing geometries are studied parametrically to identify the aerodynamic characteristics at various flight conditions. Darbe apskaiciuojama vejaracio sudaryto is skaiciuojamuju menciu generuojama galia ir stabdymo rezimo atakos kampu reiksmes. Atlikus modeliavima, ivertinant menciu sukimosi dazni, gautos darbines sukimo momentu kreives. Pagal gautus rezultatus rasti mentes veikiantys sukimo momentai ir menciu atakos kampai, kuriu deka gaunamos maksimalios sukimo momentu reiksmes. Analize atlikta keiciant mentes padeti oro srauto atzvilgiu, kad butu galima nustatyti optimalius atakos kampus. Straipsnyje pateiktas modeliavimo programa Solidworks Flow Simulation atlikta asimetrinio ir simetrinio profiliu menciu srautu analize esant skirtingiems oro srauto greiciams. Keywords: wind power plant, blade, flow, angle of attack (pitching). This analysis indicated that the asymmetrical blade generates a bigger torque and power than the same chord length blade of a symmetrical profile. Angle of attack values under braking conditions and power generated by rotor of analyzed blades were estimated. During designing process the graphs of operating torque were obtained according to an evaluation of blades' rotation frequency. The results were analyzed to identify torques and angles of attack affecting the blades, which allowed deriving the maximum torque values.
The analysis was carried out by changing the blade's position in respect of the airflow in order to determine the optimum angles of attack.
Abstract : The article presents using flow designing fluid simulation software SolidWorks Flow Simulation flow analysis of symmetrical and asymmetrical profile blades at different airflow velocities was performed.