Boundary layer transition model
US7251592B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 18, 2004 |
| Grant date | Jul 31, 2007 |
| Priority date | — |
| Expiry date | Dec 6, 2024 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG06F2111/10
- WIPO fieldComputer technology
- WIPO sectorElectrical engineering
Abstract
A method for analyzing performance of an airfoil includes determining: an estimated laminar separation location; a freestream turbulence intensity; a momentum thickness; and a turbulence length scale. Based upon the freestream turbulence intensity, momentum thickness, and turbulence length scale, a first momentum thickness Reynolds number associated with a first estimated laminar/turbulent boundary transition location along the airfoil is determined. If the estimated laminar separation location is downstream of the first estimated transition, the first estimated transition is used to determine a spatial domain for running a turbulent flow model. If the estimated laminar separation location is upstream of the first estimated transition, a second estimated transition location is used to determine a spatial domain for running the turbulent flow model. The second estimated transition location is determined as a function of a momentum thickness Reynolds number associated with the estimated laminar separation location.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.