Collaborative Research: Effects of wall curvature on hypersonic turbulent spatially-developing boundary layers
Abstract
In this project we seek to develop a robust turbulent in flow generation methodology for hypersonic (Mach numbers up to 5) spatially-developing turbulent boundary layers (SDTBL) in a suite of Direct Numerical Simulations (DNS) with high spatial/temporal resolution as well as Large Eddy Simulations (LES) at high Reynolds numbers. The prescription ofaccurate in flow turbulent conditions will be used to evaluate the downstream influence of convex(favorable pressure gradient) and concave (adverse pressure gradient) wall curvatures on low/highorder statistics of flow parameters (velocity, density, pressure and temperature), intermittency, energy budget, power spectra of velocity/temperature fluctuations and the strong Reynolds analogy(SRA) relations. Furthermore, the extensive information supplied by DNS will allow us: i) to assessthe impact of wall-curvature driven pressure gradients on the large-scale structures, and ii) to pro-pose (improve) new (existent) sub-grid scale (SGS) turbulence models for LES. Thus, the acquiredunderstanding of the physics behind curved walls will lead to the development of flow/heat transfer control tools on hypersonic vehicle design. The proposed finite-element flow solver (PHASTA) has been able to simulate complex geometries (in this study, curved walls) and has shown a great scalability for petascale computing in more than 512,000 cores in Mira (Argonne s 10-Petaflop Supercomputer). To our knowledge, the proposed petascale DNS/LES study on hypersonic boundary layers on complex geometries and high Reynolds numbers will be carried out for thefirst time.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Feb 06, 2017
- Source ID
- FA95501710051
Entities
People
- Juan Araya
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Puerto Rico at Mayaguez