Direct numerical simulation of the Gaussian (Boeing) Bump: Separated flow region
ORAL
Abstract
Direct Numerical Simulation of a turbulent boundary layer over the Gaussian (Boeing) bump is performed at ReL = 2 million (based on the tunnel width L which corresponds to Reh=170,000 based on the bump height). This simulation will be contrasted with prior published results at ReL=1 million case (same geometry at half the speed) where the flow did not separate due to re-laminarization and re-transition. At 2 million the flow remains turbulent and separates soon after the onset of a strong adverse pressure gradient just past the bump apex. Velocity, Reynolds stresses, spectra, and turbulent kinetic energy budgets from the post-separation region of the flow will be presented and discussed. In this region, we also analyze the flow in a streamline-aligned coordinate system to better understand its flow physics.
*The authors would like to acknowledge the Transformational Tools and Technologies Project of the National Aeronautics and Space Administration (NASA) 80NSSC18M0147 for funding of this work. Moreover, this research used computational resources of the NASA High-End Computing (HEC) Program through the NASA Advanced Supercomputing (NAS) Division at Ames Research Center as well as the Argonne Leadership Computing Facility which is a DOE Office of Science User Facility supported under Contract DE-AC02-06CH11357.
–
Presenters
-
Kenneth E Jansen
- University of Colorado, Boulder