A hybrid structured-unstructured grid method for aerodynamic flow simulations

1995 ◽  
Author(s):  
Torsten Berglind
Keyword(s):  
Unstructured Grid ◽  
Grid Method ◽  
Flow Simulations

Some challenges of realistic flow simulations by unstructured grid CFD

2003 ◽  
Vol 43 (6-7) ◽  
pp. 769-783 ◽  
Author(s):  
Kazuhiro Nakahashi ◽  
Yasushi Ito ◽  
Fumiya Togashi
Keyword(s):  
Unstructured Grid ◽  
Flow Simulations

scholarly journals Numerical Analysis of Scramjet Internal Flow by Hybrid Unstructured Grid Method.

2000 ◽  
Vol 43 (3) ◽  
pp. 407-413
Author(s):  
Masatoshi KODERA ◽  
Yasutaka IGARASHI ◽  
Kazuhiro NAKAHASHI ◽  
Takeshi KANDA ◽  
Tetsuo HIRAIWA ◽  
...  
Keyword(s):  
Numerical Analysis ◽  
Unstructured Grid ◽  
Grid Method ◽  
Internal Flow

Numerical Simulations of Three Dimensional Turbulent Flows in a Shrouded Backswept Impeller at Design and Off-Design Flow Rates Using Unstructured Grid Method

2000 ◽  
Author(s):  
Chuhua Zhang ◽  
Yongmiao Miao ◽  
Chuangang Gu
Keyword(s):  
Flow Velocity ◽  
Flow Rate ◽  
Unstructured Grid ◽  
Three Dimensional ◽  
Grid Method ◽  
Main Flow ◽  
Design Flow ◽  
Radial Velocity Component ◽  
Flow Rates ◽  
Design Flow Rate

The three-dimensional turbulent flow fields in a shrouded fan impeller with backswept discharge at three operating flow rates are numerically calculated with an unstructured grid method recently developed by the authors. Reynolds-averaged Navier-Stokes (N-S) equations and k-ε equations are solved through finite volume method with pressure correction algorithm. Numerical results are presented for detailed main and secondary flow velocity. The agreements of radial velocity component at different sections at design flow rate between computations and measurements are generally good. It can be observed that different flow rates have distinctive effects on flow patterns. At design flow rate, the flow is behaved as attached flow pattern and has a relatively smooth distribution for the main flow velocity. Above the design flow rate, a sudden drop and non-smooth distribution for the main flow velocity appear at the pressure-hub corner near the impeller inlet, however, the distribution of main flow velocity becomes smooth gradually downstream. Under the design flow rate, the jet-wake structure appears obviously within the impeller passage.

scholarly journals Transonic Turbomachinery Calculations Using a Hybrid Structured-Unstructured Grid Method

1994 ◽  
Author(s):  
Scott M. Richardson
Keyword(s):  
Unstructured Grid ◽  
Unstructured Mesh ◽  
Stokes Equations ◽  
Three Dimensional ◽  
Grid Method ◽  
Navier Stokes ◽  
Flow Equations ◽  
Transonic Compressor ◽  
Flow Features ◽  
Grid Points

A method is presented for solving the two-dimensional Navier-Stokes equations on a solution-adaptive grid of both structured and unstructured meshes. Flow near airfoil surfaces is modeled using an implicit finite difference algorithm on a structured O-type mesh. The flow equations in the blade passages are written in a cell-vertex finite volume formulation and are solved on an unstructured mesh using a Runge-Kutta explicit algorithm. Both the structured and unstructured grid also include solution dependent adaptation to allow resolution of flow features with a minimum of grid points. The structured mesh divides to locally add grid lines, while the unstructured mesh allows the addition or removal of individual cells. An overlapping interface region is used to conservatively communicate flow variable information between the two grids. The quasi-three-dimensional effects of streamtube contraction and radius change are included to allow calculation of modern turbomachine designs. A study is included to determine the effect on cacade parameters of inclusion of viscous terms in the solution of the flow equations in the unstructured domain. Quasi-three-dimensional computations of flow through a transonic compressor and turbine cascade are compared with experimental data.

Sign in / Sign up

Export Citation Format

Share Document