Singularity method applied to the classical Helmholtz flow coupling procedure with boundary layer calculation

Ph. Legallais; J. Hureau

doi:10.1051/jp3:1994186

Flow analysis in two-dimensional impeller of centrifugal pump by the surface singularity method combined with a flow-model of three-dimensional boundary layer.

TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series B ◽

10.1299/kikaib.53.3038 ◽

1987 ◽

Vol 53 (494) ◽

pp. 3038-3043

Author(s):

Akinori FURUKAWA ◽

Ci-Chang CHENG ◽

Takakichi SEKIYA ◽

Yasuo TAKAMATSU

Keyword(s):

Boundary Layer ◽

Centrifugal Pump ◽

Flow Model ◽

Flow Analysis ◽

Three Dimensional ◽

Surface Singularity ◽

Two Dimensional ◽

Singularity Method ◽

Dimensional Boundary

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Survey on the Indirect Methods of Potential Flow Used for the Optimization of Airships Profile

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.554.717 ◽

2014 ◽

Vol 554 ◽

pp. 717-723

Author(s):

Reza Abbasabadi Hassanzadeh ◽

Shahab Shariatmadari ◽

Ali Chegeni ◽

Seyed Alireza Ghazanfari ◽

Mahdi Nakisa

Keyword(s):

Boundary Layer ◽

Turbulent Boundary Layer ◽

Flow Field ◽

Drag Coefficient ◽

Body Surface ◽

Potential Flow ◽

The Body ◽

Indirect Methods ◽

Singularity Method ◽

Singularity Distribution

The present study aims to investigate the optimized profile of the body through minimizing the Drag coefficient in certain Reynolds regime. For this purpose, effective aerodynamic computations are required to find the Drag coefficient. Then, the computations should be coupled thorough an optimization process to obtain the optimized profile. The aerodynamic computations include calculating the surrounding potential flow field of an object, calculating the laminar and turbulent boundary layer close to the object, and calculating the Drag coefficient of the object’s body surface. To optimize the profile, indirect methods are used to calculate the potential flow since the object profile is initially amorphous. In addition to the indirect methods, the present study has also used axial singularity method which is more precise and efficient compared to other methods. In this method, the body profile is not optimized directly. Instead, a sink-and-source singularity distribution is used on the axis to model the body profile and calculate the relevant viscose flow field.

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Boundary layer—inviscid flow coupling

The Finite Element Method Set ◽

10.1016/b978-075066431-8/50238-1 ◽

2005 ◽

pp. 409-412

Author(s):

O ZIENKIEWICZ ◽

R TAYLOR ◽

J ZHU

Keyword(s):

Boundary Layer ◽

Inviscid Flow ◽

Flow Coupling

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The Numerical Simulation of the Single Abrasive Motion Law in the Environment of Structural Surface

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.102-104.573 ◽

2010 ◽

Vol 102-104 ◽

pp. 573-577 ◽

Cited By ~ 1

Author(s):

Shi Ming Ji ◽

Bao Li Ma ◽

Da Peng Tan ◽

Qiao Ling Yuan

Keyword(s):

Numerical Simulation ◽

Boundary Layer ◽

Flow Field ◽

Surface Effect ◽

Computational Method ◽

Motion Trajectory ◽

Two Phase ◽

Leading Role ◽

Turbulence Flow ◽

Flow Coupling

As far as the controllability of turbulence flow field surface effect of the soft abrasive flow was concerned, to begin with the analysis of the motion of the particle in the flow field, the paper studied the motion law of particle in the flow field, especially in the boundary layer. Based on the fluid-solid two-phase flow coupling style, it established the single particle dynamics model. Then it established the realizable k-ε model, in the light of the numerical simulation of turbulent flow. With the adoption of the computational method of SIMPLEC, it asked for the velocity and the pressure of fluid in the U-shaped flow passage, the velocity and the motion law of particles with different granularities and velocity, in the boundary layer. Experimentation results tell us that the original velocity plays a leading role in the motion trajectory of particles. The diameter influenced the particles motion trajectory in some degree.

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The Design of Shock-Free Compressor Cascades Including Viscous Boundary-Layer Effects

Journal of Turbomachinery ◽

10.1115/1.3262204 ◽

1988 ◽

Vol 110 (3) ◽

pp. 354-362 ◽

Cited By ~ 1

Author(s):

A. A. Hassan

Keyword(s):

Boundary Layer ◽

Numerical Procedure ◽

Transition To Turbulence ◽

Viscous Effects ◽

Compressor Blades ◽

Viscous Boundary Layer ◽

Design Algorithm ◽

Transonic Compressor ◽

Coupling Procedure ◽

Hodograph Plane

A numerical procedure has been developed for the design of shock-free transonic compressor cascades with an allowance for viscous effects, providing that the boundary layer is fully attached over the blade. The method described combines, in an iterative process, a modified inviscid hodograph-based inverse-design algorithm (CIDA), originally developed by the author for the design of shock-free airfoils, and the inverse boundary-layer algorithm (LTBLCEQL) of Miner et al. [22]. In the numerical procedure, the inviscid subsonic and supersonic regions of the flow are decoupled allowing the solution of either an elliptic or hyperbolic-type partial differential equation for the full stream function. For the subcritical portion of the flow, the inviscid calculation is performed in a computational plane which is obtained through a sequence of conformal and numerical transformations of the two-sheeted hodograph plane. For the supercritical portion, a characteristic calculation is carried out in the hodograph plane. The results are then mapped back to the physical plane to determine the inviscid blade configuration. Viscous effects are then incorporated via the boundary-layer displacement surface concept. The boundary-layer algorithm incorporates a two-layer eddy viscosity turbulence model and allows for gradual, rather than instantaneous, transition to turbulence. Two examples of shock-free compressor blades are given to demonstrate the capabilities of the numerical coupling procedure.

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