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In the present study, the effect of hinge position (H) has been numerically investigated to find the appropriate position for improving the aerodynamic performance of the NACA 0012 flapped airfoil. In addition, perpendicular and tangential suctions have been applied to control the flow separation and enhance the aerodynamic performance over the NACA 0012 flapped airfoil at each different hinge positions. The simulations were carried out at a Reynolds number of 5 × 10 5 (Ma = 0.021) based on two-dimensional incompressible unsteady Reynolds-averaged Navier-Stokes calculations to determine the adequate hinge position. The turbulence was modeled using the shear stress transport k-ω turbulence model. The effect of perpendicular suction (θ jet = − 90°) and tangential suction (θ jet = − 30°) was computationally studied over NACA 0012 flapped airfoil for five different hinge positions (H = 0.7c, 0.75c, 0.8c, 0.85c and 0.9c) and a flap deflection (δ f) of 15°. Based on the results, the hinge position significantly affects the aerodynamic performance of the airfoil. The lift coefficient increased clearly as the hinge position moved to the trailing edge of the airfoil. Using perpendicular suction caused to increase the lift coefficient and decrease the drag coefficient. Consequently, the maximum value of the lift-to-drag ratio (C L /C D) for perpendicular and tangential suctions was achieved about 35.8% and 25.1% higher than that of the case without suction at an angle of attack of 12° and H = 0.9c. Also, the effect of perpendicular suction was more considerable compared to the tangential suction. This caused a reduction in the size of the recirculation zone from 0.5 to 0.09 of the airfoil chord length and also transferred it from 1.13 to 1.18 of the airfoil chord length.

In the present study, a numerical simulation of turbulent flow over the NACA 65-100 compressor cascade was conducted to control the boundary layer using both suction and blowing separately. In order to study the effects of suction and blowing over the blade, 10 slots were considered on the upper surface of the blade. The slots were considered at intervals of 5% to 95% of the blade chord length. The results showed that applying both suction and blowing caused to delay the flow separation point and move it downstream which led to increase the lift coefficient and decrease the drag coefficient. Also, it was concluded that the effect of applying suction especially in the location where is near the trailing edge was significantly more than the effect of applying blowing. So that the lift coefficient had increased about 45% at 95% of chord length for suction compared to 5% of chord length and it had increased about 10% at 95% of chord length for blowing compared to 5% of chord length. Moreover, the best location to apply suction and blowing in a compressor cascade was near the flow separation point where is near the trailing edge.

In the past decades, desiccant cooling systems have received much attention. These systems are considered as an alternative way to decrease energy consumption and greenhouse gas emission in humid and hot locations. To address the importance of desiccant air-conditioning systems, the present research aims to provide an overview of recent studies on the development of desiccant air conditioning system. Another objective is to consider the numerical and theoretical analysis of desiccant systems. Moreover, for the first time, a summary of recent researches regarding the use of Computational Fluid Dynamics (CFD) technique for numerical modeling of desiccant cooling systems has been especially reviewed in detail. Finally, in the present review, the principle of regeneration of liquid desiccant using solar energy have also been considered briefly.

Due to the lower energy consumption in the evaporative cooling, it is the subject of numerous studies. Evaporative cooling considers a green cooling system which does not require any chemical reaction and does not depend on the hazardous material. The present study mainly focused on parametric analysis of an indirect evaporative cooling system using the computational fluid dynamics method. The numerical simulation of an indirect evaporative cooling system was carried out using ANSYS Fluent 18.2. The effects of the water inlet velocity, air inlet velocity, coil diameters (d c ) and the number of the heat exchanger copper coils were numerically investigated. The flow was considered as threedimensional, turbulent, and incompressible. The results indicated that the increment of the coil diameter and water inlet velocity had a positive effect on the performance of the indirect evaporative cooling system. The maximum water outlet temperature was obtained at 285.05 K for the water inlet velocity of 0.5 m/s. Moreover, the saturation efficiency is decreased by increasing air inlet velocity. On the other hand, saturation efficiency was increased at all air inlet velocities by increasing the coil diameter.

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This study mainly focused on the comparison of the effect of single and simultaneous suction and blowing jets on the aerodynamic performance of an airfoil with/without flap to evaluate the most effective flow control configuration using computational fluid dynamics (CFD) method. Moreover, the effect of applying single and simultaneous jets have been conducted on delaying and controlling the flow separation. The results were obtained using two-dimensional incompressible Unsteady Reynolds-Averaged Navier-Stokes (URANS), and the turbulence was simulated with SST k-x turbulence model. Also, different parameters including two jet locations (L jet), three jet velocity ratios (R jet), three jet angles (h jet) and three flap deflections (d f) were analyzed to find the most effective case of applying flow control jets to delay the boundary layer separation. It was concluded that applying a single suction jet and simultaneous suction and blowing jets on the flapped airfoil was more effective to improve the lift-to-drag ratio (C L /C D) than applying these jets to the without flap case. The maximum value of C L /C D was achieved by single suction jet for the without flap case which was equal to 73.7. The maximum increment of stall angle over the without flap airfoil and flapped airfoil was obtained by applying single suction jet, which increased the stall angle from 14°to 20°and 14°to 16°for the suction angle of-90°a nd suction velocity ratio of 0.15, respectively.