Direct Numerical Simulation Database for Supersonic and Hypersonic Turbulent Boundary Layers
This paper presents a direct numerical simulation database of high-speed zero-pressure-gradient turbulent boundary layers developing spatially over a flat plate with nominal freestream Mach number ranging from 2.5 to 14 and wall-to-recovery temperature ranging from 0.18 to 1.0. The flow conditions of the DNS are representative of the operational conditions of the Purdue Mach 6 quiet tunnel, the Sandia Hypersonic Wind Tunnel at Mach 8, and the AEDC Hypervelocity Tunnel No. 9 at Mach 14. The DNS database is used to gauge the performance of compressibility transformations, including the classical Morkovin's scaling and strong Reynolds analogy as well as the newly proposed mean velocity and temperature scalings that explicitly account for wall heat flux. Several insights into the effect of direct compressibility are gained by inspecting the thermodynamic fluctuations and the Reynolds stress budget terms. Precomputed flow statistics, including Reynolds stresses and their budgets, will be available at the website of the NASA Langley Turbulence Modeling Resource, allowing other investigators to query any property of interest.
C. Zhang et al., "Direct Numerical Simulation Database for Supersonic and Hypersonic Turbulent Boundary Layers," AIAA Journal, vol. 56, no. 11, pp. 4297-4311, American Institute of Aeronautics and Astronautics (AIAA), Sep 2018.
The definitive version is available at https://doi.org/10.2514/1.J057296
Mechanical and Aerospace Engineering
Keywords and Phrases
Budget control; Compressibility; Database systems; Direct numerical simulation; Heat flux; NASA; Numerical models; Query processing; Reynolds number; Turbulence; Turbulent flow; Wind tunnels, Freestream mach number; Hypersonic wind tunnels; Operational conditions; Recovery temperature; Supersonic and hypersonic; Thermodynamic fluctuations; Turbulent boundary layers; Zero-pressure gradient turbulent boundary layer, Hypersonic boundary layers
International Standard Serial Number (ISSN)
Article - Journal
© 2018 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Sep 2018