The flow of an electroconductive incompressible ternary hybrid nanofluid with heat conduction in a boundary layer including metallic nanoparticles (NPs) over an extended cylindrical with magnetic induction effects is reported in this research. The ternary hybrid nanofluid has been synthesized with the dispersion of titanium dioxide, cobalt ferrite, and magnesium oxide NPs in the base fluid water. For a range of economical and biological applications, a computational model is designed to augment the mass and energy conveyance rate and promote the performance and efficiency of thermal energy propagation. The model has been written as a system of partial differential equations. Which are simplified to the system of ordinary differential equations through similarity replacements. The computing approach parametric continuation method is used to further process the resultant first order differential equations. The results are validated with the bvp4c package for accuracy and validity. The outcomes are displayed and analyzed through Figures and Tables. It has been observed that the inverse Prandtl magnetic number and a larger magnetic constant reduce the fluid flow and elevate the energy profile. The variation of ternary hybrid NPs significantly boosts the thermophysical features of the base fluid.

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Computational Valuation of Darcy Ternary-Hybrid Nanofluid Flow across an Extending Cylinder with Induction Effects

Power improvement of NREL 5-MW wind turbine using multi-DBD plasma actuators

Turbulent boundary layer separation control using plasma actuator at Reynolds number 2000000

Experimental characteristics of a two-electrode plasma synthetic jet actuator array in serial

Leading-edge flow separation control over an airfoil using a symmetrical dielectric barrier discharge plasma actuator

The effectiveness of asymmetrical and symmetrical plasma actuators for enhancing the aerodynamic performances of a wing has been investigated through the flow separation control experiment in a low-speed wind tunnel. The asymmetrical plasma actuator is a typical single dielectric barrier discharge plasma actuator and induces a one-way airflow. Compared with the asymmetrical dielectric barrier discharge actuator, the symmetrical actuator produced a bidirectional tangential jet. The two actuators were mounted on the leading edge of a wing and oriented along the spanwise direction to produce a body force in the streamwise direction. Force measurements show that the symmetrical actuator can effectively delay the flow separation on the wing at the wind speed up to 100  m/s and has a better control performance than that of the asymmetrical actuator. Particle image velocimetry experiments are carried out to identify the different control mechanisms between the two actuators and highlights how the induced airflow...

Wing Flow Separation Control Using Asymmetrical and Symmetrical Plasma Actuator

Flow control study of a circular cylinder is carried out using symmetric dielectric barrier discharge (DBD) plasma actuators at the Reynolds number of 10,000. Here, two symmetric DBD plasma actuators are located at the top and bottom of the circular cylinder, respectively, each of which induces pairs of counter-rotating starting vortices on both sides of exposed electrodes. The downstream starting vortices soon take the form of a wall jet along the freestream direction. On the other hand, the upstream starting vortices interact with the incoming flow remain for some time, bringing in high momentum from the freestream to near-wall region, enabling the boundary layer to withstand the adverse pressure gradient and suppressing the separation around the circular cylinder. The rotating vortical structures around the circular cylinder created by the plasma actuators lead to a reduction in the drag coefficient of up to 25%, providing a similar effect to moving surface boundary layer control (MSBLC). This configuration of symmetric DBD plasma actuator, which is studied for the first time in this investigation, is, therefore, called virtual MSBLC. Our results also indicated that the control effect of virtual MSBLC can be enhanced with an increase in the momentum coefficient of plasma jet. Unlike traditional MSBLC devices, the virtual MSBLC based on symmetric DBD plasma actuators do not have profile drag and are without complicated mechanical systems.

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Flow control over a circular cylinder using virtual moving surface boundary layer control

The present paper described an experimental investigation of separation control of an Unmanned Aerial Vehicle (UAV) at high wind speeds. The plasma actuator was based on Dielectric Barrier Discharge (DBD) and operated in a steady manner. The flow over a wing of UAV was performed with smoke flow visualization in the ϕ0.75 m low speed wind tunnel to reveal the flow structure over the wing so that the locations of plasma actuators could be optimized. A full model of the UAV was experimentally investigated in the ϕ3.2 m low speed wind tunnel using a six-component internal strain gauge balance. The effects of the key parameters, including the locations of the plasma actuators, the applied voltage amplitude and the operating frequency, were obtained. The whole test model was made of aluminium and acted as a cathode of the actuator. The results showed that the plasma acting on the surface of UAV could obviously suppress the boundary layer separation and reduce the model vibration at the high wind speeds. It was found that the maximum lift coefficient of the UAV was increased by 2.5% and the lift/drag ratio was increased by about 80% at the wind speed of 100 m/s. The control mechanism of the plasma actuator at the test configuration was also analyzed.

Yong Huang

Papers

Turbulent boundary layer separation control using plasma actuator at Reynolds number 2000000

Leading-edge flow separation control over an airfoil using a symmetrical dielectric barrier discharge plasma actuator

Wing Flow Separation Control Using Asymmetrical and Symmetrical Plasma Actuator

Flow control over a circular cylinder using virtual moving surface boundary layer control

Unmanned air vehicle flow separation control using dielectric barrier discharge plasma at high wind speed