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

An introduction to heat transfer

https://profdoc.um.ac.ir/articles/a/1057659.pdf

Collision partner selection schemes in DSMC: From micro/nano flows to hypersonic flows

Dual fuel consumption and efficiency of marine steam generators for the propulsion of LNG carrier

Energy and exergy analysis of the turbo-generators and steam turbine for the main feed water pump drive on LNG carrier

In this study, rarefied supersonic and subsonic gas flow around a NACA 0012 airfoil is simulated using both continuum and particle approaches. Navier–Stokes equations subject to the first order slip/jump boundary conditions are solved under the framework of OpenFOAM package. The DSMC solver of the package, i.e., dsmcFoam, has been improved to include a newly presented “simplified Bernoulli trial (SBT)” scheme for inter-molecular collision modeling. The use of SBT collision model permits to obtain accurate results using a much lower number of simulator particles. We considered flow at different angles of attacks and Knudsen numbers at both the subsonic and supersonic regimes. The computed density and surface pressure distributions are compared with the experimental and numerical data and suitable accuracy was observed. We investigate variations of the lift and drag coefficients with the Knudsen number and angle of attack. At low Kn number in supersonic regime, our results for lift coefficient agree well with the linearized theory; however, the deviation starts as soon as the angle of attack goes beyond 15 ° or shock wave forms above the airfoil. Along with this, we have observed that drag coefficient increases with the Kn number increasing. We also investigated the effect of Kn number on the leading edge shock position and structure, drag polar ( C L / C D ) , and slip velocity over the airfoil.

https://profdoc.um.ac.ir/articles/a/1041045.pdf

Investigation of aerodynamic characteristics of rarefied flow around NACA 0012 airfoil using DSMC and NS solvers

Mass ratio effect on vortex induced vibration of a flexibly mounted circular cylinder, an experimental study

https://profdoc.um.ac.ir/articles/a/1047268.pdf

Numerical investigation on the lifetime decline of burners in a wall-fired dual-fuel utility boiler

Savonius turbines have been the subject of various wind energy projects due to their good starting characteristics, easy installation, and independency of wind direction. However, the Savonius roto...

/pdf/experimental-and-numerical-investigations-on-the-aerodynamic-14dgpa2m85.pdf

Experimental and numerical investigations on the aerodynamic performance of a pivoted Savonius wind turbine

In this study, a three-bladed pivoted vertical axis Savonius wind turbine is subjected to numerical and experimental studies. The experiments are carried out in a subsonic open-jet type wind tunnel, where the instantaneous position of the opening/closing blades are also determined via high speed imaging. The effects of adding end plates and the rotor aspect ratio on the turbine torque and power coefficients are investigated experimentally. Results show that adding end plates greatly enhances the rotor aerodynamic performance, in terms of both the maximum power coefficient and also the working range of the turbine. Similar effects are also observed for the effects of increasing the aspect ratio. Comparing numerical results with the experimental data demonstrated that the numerical results are in a convincing agreement with the experimental data of a wind rotor with an aspect ratio of 2.0 equipped with end plates. Although there are several two-dimensional numerical simulations for the drag-based vertical axis wind turbines in the literature, the results of the current study suggests that two-dimensional numerical results are not comparable with the experimental data of the rotors with small aspect ratios, especially without end plates.

https://jafmonline.net/JournalArchive/download?file_ID=49101&issue_ID=256

Mohsen Kahrom

Papers

Investigation of aerodynamic characteristics of rarefied flow around NACA 0012 airfoil using DSMC and NS solvers

Mass ratio effect on vortex induced vibration of a flexibly mounted circular cylinder, an experimental study

Numerical investigation on the lifetime decline of burners in a wall-fired dual-fuel utility boiler

Experimental and numerical investigations on the aerodynamic performance of a pivoted Savonius wind turbine

Aerodynamic Analysis of a Three-Bladed Pivoted Savonius Wind Turbine: Wind Tunnel Testing and Numerical Simulation