The boundary layer equations for plane, incompressible, and steady flow are 

$$\matrix{ {u{{\partial u} \over {\partial x}} + v{{\partial u} \over {\partial y}} = - {1 \over \varrho }{{\partial p} \over {\partial x}} + v{{{\partial ^2}u} \over {\partial {y^2}}},} \cr {0 = {{\partial p} \over {\partial y}},} \cr {{{\partial u} \over {\partial x}} + {{\partial v} \over {\partial y}} = 0.} \cr }$$

Boundary Layer Theory

Proposal and assessment of a novel supercritical CO2 Brayton cycle integrated with LiBr absorption chiller for concentrated solar power applications

Thermo-economic analysis and sizing of a PV plant equipped with a compressed air energy storage system

Energy consumption minimization in an innovative hybrid power production station by employing PV and evacuated tube collector solar thermal systems

The first and second law analysis of a grid connected photovoltaic plant equipped with a compressed air energy storage unit

Turbine air inlet cooling is one of many available commercial methods for increasing the performance of a gas turbine. The method that has different configurations could be applied for nearly all gas turbines. This paper offers a comparison between two standard and one exquisite inlet air cooling method, which are used to improve the performance of a gas turbine located at the Khangiran refinery in Iran. These methods have been applied to one of the gas turbines located at the Khangiran refinery. Two common air-cooling methods are based on fogging systems and absorption chillers. The idea behind the novel method is to utilize the potential cooling capacity of the refinery natural gas pressure drop station. The research is part of a plenary program developed to enhance the efficiency of the gas turbine used at the Khangiran gas refinery. Considering the results, it is found that the new method is the most feasible in economic terms, so it has been recommended to be used for improving the performance of the Khangiran refinery gas turbines.

Improving Khangiran gas turbine efficiency by two standard and one novel inlet air cooling method

The effects of adverse pressure gradient (APG) on turbulent boundary layer flow are studied in this article using numerical methods. The values of pressure gradient are simulated by Clauser's param...

The Effect of Adverse Pressure Gradient on the Structure of Turbulent Boundary Layer

An experimental study was carried out on the wake of a cylinder on the back of which a plate is installed parallel to the fluid flow, with different terminal angles, where the Reynolds number is 50000. At the end of the plate, blades with the height of 0.25 equal to the cylinder diameter and with 45, 90 and 135 degrees angle from the horizon, are installed where the cylinder diameter is equal to the plate length. The plate effects on the variation of drag coefficient, medium velocity profiles, reduced velocity, half of the entrance, turbulence intensity and Strouhal number are investigated. The results showed that the drag coefficient for cylinder including the plate, regardless of the end angle, is smaller than the isolated cylinder. The existence of a plate with a terminal angle of 45 degree led to more reduction in drag coefficient of the cylinder.

http://admt.iaumajlesi.ac.ir/article_534963_9722337c2aea5576c1b5a87cf030a62c.pdf

Experimental Investigation of the Flow Control of Wake Cylinder by a Plate with Different Geometrical Ends

In general, the aerodynamic stability of long span bridges is evaluated based on the results of wind tunnel tests in the low Reynolds number region, because in almost all wind tunnel tests, it is impracticable to satisfy Reynolds number similitude. Therefore, in order to correctly evaluate conventional wind tunnel test results, Reynolds number eﬀects on the aerodynamic force coeﬃcients acting on bridge decks must be carefully investigated. This paper investigate the Reynolds number effect on the aerodynamics of bridge deck section measured in the wide Reynolds number region from  to  based on the dimension of deck height in smooth flow. For the simulation of fluid flow, open-circuit and blowing wind tunnel was used for which the maximum nominal turbulence was 0.1%. The results show that increasing Reynolds number has less effect on the drag coefficient and Strouhal number and parameters in downstream of the model. In other words, variation of drag coefficient and Strouhal number is very small in Reynolds numbers over 20000. Increasing Reynolds number would not be followed with an outstanding change at value of velocity defect but causes to reduce half width, of course, it has no effect in rate growth of half width.

http://admt.iaumajlesi.ac.ir/article_534934_2bc5264cfbcef07554a65c7cda51c68f.pdf

An investigation of Reynolds number effect on the aerodynamics of bluff body with sharp edges

A numerical study has been carried out to study fluid flow within a rotor-stator system with an inward throughflow and pre-rotation. Furthermore, the effect of flow parameters on the flow structure has been investigated. The entrainment coefficient, beta, of the rotating fluid and the rotating disc moment coefficient have been calculated. A correlation has been found for predicting the place of stagnation point. The results show the Batchelor type of flow with two separated boundary layers on the rotating and stationary discs. The numerical results are compared with the available measured data and generally, a good agreement has been encountered.

https://am.ippt.pan.pl/am/article/viewFile/v62p195/pdf

Amir Bak Khoshnevis

Papers

Improving Khangiran gas turbine efficiency by two standard and one novel inlet air cooling method

The Effect of Adverse Pressure Gradient on the Structure of Turbulent Boundary Layer

Experimental Investigation of the Flow Control of Wake Cylinder by a Plate with Different Geometrical Ends

An investigation of Reynolds number effect on the aerodynamics of bluff body with sharp edges

Numerical study of flow in a rotor-stator system with inward throughflow