Direct numerical simulation of the turbulent boundary layer over the Gaussian-shaped Boeing bump at Re<sub>L</sub>=2M
ORAL
Abstract
The turbulent boundary layer over a two-dimensional Gaussian-shaped Boeing bump is computed by direct numerical simulation of the incompressible Navier–Stokes equations. At the inflow, the momentum thickness Reynolds number is approximately 1900 and the boundary layer thickness is 1/9 of the bump height. Preliminary results from this on-going simulation suggest that, at this Reynolds number, the flow does not experience significant re-laminarization and the resulting flow experiences a large separation soon after the bump peak where the pressure gradient switches from favorable to adverse. While it is unlikely that fully converged statistics will be obtained for the separated flow and recovery region in time for this presentation, the attached flow regions and early separated flow region converge much faster and the focus of the talk will be on these regions. An early assessment of the effect of simulation domain width will also be discussed.
*This work was supported by the National Aeronautics and Space Administration, Transformational Tools and Technologies grant 80NSSC18M0147, both to the University of Colorado Boulder. Computational resources were utilized at the NASA High-End Computing (HEC) Program through the NASA Advanced Supercomputing (NAS) Division at Ames Research Center and at the Argonne Leadership Computing Facility (ALCF), which is a DOE Office of Science User Facility supported under Contract DE-AC02-06CH11357.
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Presenters
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Kenneth E Jansen
- University of Colorado, Boulder