Prediction of separated transonic wing flows with nonequilibrium algebraic turbulence model
β Scribed by ABID, RIDHA; VATSA, VEER N.; JOHNSON, DENNIS A.; WEDAN, BRUCE W.
- Book ID
- 120312183
- Publisher
- American Institute of Aeronautics and Astronautics
- Year
- 1990
- Tongue
- English
- Weight
- 773 KB
- Volume
- 28
- Category
- Article
- ISSN
- 0001-1452
- DOI
- 10.2514/3.25234
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π SIMILAR VOLUMES
Turbulent flows around aerofoils and wings are simulated by solving the two-and three-dimensional Navier-Stokes equations in quadrilaterals and hexahedrons, respectively. Turbulent flow is described by an algebraic eddy viscosity model. Boundary-conforming 0-and 0-0-type meshes are generated by the
The v 2 Β±f (or kΒ±eΒ±v H2 ) model of Durbin, which has shown very good performance in several test cases with separated Β―ows at low speeds, has been applied to transonic Β―ows over the Delery bump and the RAE 2822 airfoil. In both cases, shock-induced separation occurs. The elliptic relaxation equation