Direct Numerical Simulation of Hypersonic Turbulent Boundary Layer Flow using SPARC: Initial Evaluation

Technical Report · Sun Sep 01 00:00:00 EDT 2019

DOI:https://doi.org/10.2172/1569350· OSTI ID:1569350

Wagnild, Ross Martin ^[1]; Bitter, Neal ^[1]; Fike, Jeffrey A. ^[1]; Howard, Micah ^[1]

---

1. Sandia National Laboratories (SNL), Albuquerque, NM, and Livermore, CA (United States)

This report documents the initial testing of the Sandia Parallel Aerodynamics and Reentry Code (SPARC) to directly simulate hypersonic, turbulent boundary layer flow over a sharp 7- degree half-angle cone. This type of computation involves a tremendously large range of scales both in time and space, requiring a large number of grid cells and the efficient utilization of a large pool of resources. The goal of the simulation is to mimic and verify a wind tunnel experiment that seeks to measure the turbulent surface pressure fluctuations. These data are necessary for building a model to predict random vibration loading in the reentry flight environment. A low-dissipation flux scheme in SPARC is used on a 2.7 billion cell mesh to capture the turbulent fluctuations in the boundary layer flow. The grid is divided into 115200 partitions and simulated using the Knight's Landings (KNL) partition of the Trinity system. The parallel performance of SPARC is explored on the Trinity system, as well as some of the other new architectures. Extracting data from the simulation shows good agreement with the experiment as well as a colleague's simulation. The data provide a guide for which a new model can be built for better prediction of the reentry random vibration loads.

• Research Organization: Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)
• Sponsoring Organization: USDOE National Nuclear Security Administration (NNSA)
• DOE Contract Number: AC04-94AL85000
• OSTI ID: 1569350
• Report Number(s): SAND-2019-11158; 679807
• Country of Publication: United States
• Language: English