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.


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)

0001-1452; 1533-385X

Document Type

Article - Journal

Document Version


File Type





© 2018 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

01 Sep 2018