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The Natural Laminar Flow (NLF) airfoil/wing design optimization is an efficient method which can reduce significantly turbulence skin friction by delaying transition location at high Reynolds numbers.
A suitably designed coarse LES grid produces good predictions of the mean transition location with boundary layer inflow conditions at a low computational cost.
When compared with experimental data, however, it is the boundary layer-type inflow simulation produces the better prediction of the flow statistics, including the mean transition location.
We target to improve the aerodynamic characteristics of a typical 2D airfoil profile considering also the laminar-turbulent transition location for more accurate estimation of the total drag.
For this turbine blade shape the transition location did not depend on turbulence length scale, the location is more dependent on pressure distribution, Reynolds number and turbulence intensity.
Changes in the stability characteristics of a leading-edge laminar separation bubble has a dominating influence on the boundary layer dynamics and causes an abrupt change in the transition location over the airfoil.
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The transition onset over 3D MEXICO blade is visualized and transition locations are identified.
Separation and transition locations corresponded to local minimums in heat transfer.
To test this hypothesis, we assigned each detected transition at random to an ORF probe, and compared several features of the randomly assigned transitions to these same features under the observed (not randomized) transition locations.
A generalized synchronous transit method for transition state location.
The transition state location (ΔxTSF) changes dramatically as the loading rate is varied.
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CEO of Professional Science Editing for Scientists @ prosciediting.com