UFR 2-05 Best Practice Advice: Difference between revisions
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Flow around airfoils (and blades) A-airfoil (Ma=0.15,
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== Best Practice Advice for the UFR == | == Best Practice Advice for the UFR == | ||
* Use a two-dimensional mesh of at least 256 x 64 grids, and check the grid-dependence of the results on a 512 x 128 mesh. | |||
* If possible use a second-moment closure (Reynolds stress model or algebraic stress model) rather than a one- or two-equation single-moment closure model. Models with good representation of curvature and stress anistropy effects are to be preferred. | |||
* Fix transition in advance on the upper surface at x/c=12%. Then move it systematically upstream (say to 8% and 4%) and downstream (16%, 20%) to see what happens. If attempting to ''predict'' the location of transition, be aware that this is not only very difficult but will affect most other features of the flow including the trailing-edge separation, overall circulation, and hence the effective angle of attack and the resulting pressure distribution. | |||
<font size="-2" color="#888888">© copyright ERCOFTAC 2004</font><br /> | <font size="-2" color="#888888">© copyright ERCOFTAC 2004</font><br /> | ||
Revision as of 10:13, 11 March 2009
Flow around airfoils (and blades) A-airfoil (Ma=0.15,
Re/m=2x106)
Underlying Flow Regime 2-05 © copyright ERCOFTAC 2004
Best Practice Advice
Best Practice Advice for the UFR
- Use a two-dimensional mesh of at least 256 x 64 grids, and check the grid-dependence of the results on a 512 x 128 mesh.
- If possible use a second-moment closure (Reynolds stress model or algebraic stress model) rather than a one- or two-equation single-moment closure model. Models with good representation of curvature and stress anistropy effects are to be preferred.
- Fix transition in advance on the upper surface at x/c=12%. Then move it systematically upstream (say to 8% and 4%) and downstream (16%, 20%) to see what happens. If attempting to predict the location of transition, be aware that this is not only very difficult but will affect most other features of the flow including the trailing-edge separation, overall circulation, and hence the effective angle of attack and the resulting pressure distribution.
© copyright ERCOFTAC 2004
Contributors: Peter Voke - University of Surrey