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Direct Numerical Simulation Database for Hypersonic Turbulent Boundary Layers.

Chao Zhang1, Lian Duan1, Meelan M Choudhari2

  • 1Missouri University of Science and Technology, Rolla, MO 65409.

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Summary

This study presents a direct numerical simulation database for high-speed turbulent boundary layers. The data aids in evaluating compressibility transformations for hypersonic flow research.

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Area of Science:

  • Fluid dynamics
  • Turbulence research
  • Hypersonic flow

Background:

  • High-speed turbulent boundary layers are crucial in aerospace applications.
  • Understanding compressibility effects is vital for accurate flow modeling.
  • Existing scaling laws may not fully capture complex high-speed flow phenomena.

Purpose of the Study:

  • To create a comprehensive direct numerical simulation (DNS) database for high-speed zero-pressure-gradient turbulent boundary layers.
  • To evaluate the performance of various compressibility transformations.
  • To gain insights into the impact of direct compressibility on flow physics.

Main Methods:

  • Direct numerical simulation (DNS) of turbulent boundary layers over a flat plate.
  • Simulations cover Mach numbers from 2.5 to 14 and varying wall-to-recovery temperature ratios.
  • Analysis of thermodynamic fluctuations and Reynolds stress budget terms.

Main Results:

  • A DNS database is established, covering a wide range of hypersonic flow conditions.
  • The performance of Morkovin's scaling, strong Reynolds analogy, and new heat-flux-dependent scalings are assessed.
  • Insights into compressibility effects on turbulence structure are obtained.

Conclusions:

  • The DNS database provides a valuable resource for validating turbulence models in hypersonic flows.
  • The study highlights the importance of considering wall heat flux in compressibility transformations.
  • The findings contribute to a better understanding of high-speed aerodynamic flows.