DNS of transition to turbulence in a hypersonic boundary layer

Pramod K Subbareddy; Graham V. Candler

doi:10.2514/6.2011-3564

DNS of transition to turbulence in a hypersonic boundary layer

Aerospace Engineering and Mechanics

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

10 Scopus citations

Abstract

We perform direct numerical simulations (DNS) of transition to turbulence in a hypersonic boundary layer flow. The flow conditions correspond to a Mach 6, cold-wall flow with a wall temperature to adiabatic temperature ratio (T_w/T_aw) of around 0.16. Themomentum thickness Reynolds number Re_θ goes up to around 6000 at the end of the computed turbulent zone. Comparisons are made to empirical skin-friction and heat transfer coefficients. We find that the Van Driest II and Eckert correlations work best along with a Reynolds Analogy Factor of ≈ 1.2. Statistics from the mean and fluctuating turbulent flow fields are briefly discussed. The hope is that the DNS database generated will be useful for physics based improvements of RANS and LES models.

Original language	English (US)
Title of host publication	41st AIAA Fluid Dynamics Conference and Exhibit
Publisher	American Institute of Aeronautics and Astronautics Inc.
ISBN (Print)	9781600869471
DOIs	https://doi.org/10.2514/6.2011-3564
State	Published - 2011
Event	41st AIAA Fluid Dynamics Conference and Exhibit 2011 - Honolulu, HI, United States Duration: Jun 27 2011 → Jun 30 2011

Publication series

Name	41st AIAA Fluid Dynamics Conference and Exhibit

Conference

Conference	41st AIAA Fluid Dynamics Conference and Exhibit 2011
Country/Territory	United States
City	Honolulu, HI
Period	6/27/11 → 6/30/11

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10.2514/6.2011-3564

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Subbareddy, PK & Candler, GV 2011, DNS of transition to turbulence in a hypersonic boundary layer. in 41st AIAA Fluid Dynamics Conference and Exhibit. 41st AIAA Fluid Dynamics Conference and Exhibit, American Institute of Aeronautics and Astronautics Inc., 41st AIAA Fluid Dynamics Conference and Exhibit 2011, Honolulu, HI, United States, 6/27/11. https://doi.org/10.2514/6.2011-3564

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title = "DNS of transition to turbulence in a hypersonic boundary layer",

abstract = "We perform direct numerical simulations (DNS) of transition to turbulence in a hypersonic boundary layer flow. The flow conditions correspond to a Mach 6, cold-wall flow with a wall temperature to adiabatic temperature ratio (Tw/Taw) of around 0.16. Themomentum thickness Reynolds number Reθ goes up to around 6000 at the end of the computed turbulent zone. Comparisons are made to empirical skin-friction and heat transfer coefficients. We find that the Van Driest II and Eckert correlations work best along with a Reynolds Analogy Factor of ≈ 1.2. Statistics from the mean and fluctuating turbulent flow fields are briefly discussed. The hope is that the DNS database generated will be useful for physics based improvements of RANS and LES models.",

author = "Subbareddy, \{Pramod K\} and Candler, \{Graham V.\}",

year = "2011",

doi = "10.2514/6.2011-3564",

language = "English (US)",

isbn = "9781600869471",

series = "41st AIAA Fluid Dynamics Conference and Exhibit",

publisher = "American Institute of Aeronautics and Astronautics Inc.",

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note = "41st AIAA Fluid Dynamics Conference and Exhibit 2011 ; Conference date: 27-06-2011 Through 30-06-2011",

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T1 - DNS of transition to turbulence in a hypersonic boundary layer

AU - Subbareddy, Pramod K

AU - Candler, Graham V.

PY - 2011

Y1 - 2011

N2 - We perform direct numerical simulations (DNS) of transition to turbulence in a hypersonic boundary layer flow. The flow conditions correspond to a Mach 6, cold-wall flow with a wall temperature to adiabatic temperature ratio (Tw/Taw) of around 0.16. Themomentum thickness Reynolds number Reθ goes up to around 6000 at the end of the computed turbulent zone. Comparisons are made to empirical skin-friction and heat transfer coefficients. We find that the Van Driest II and Eckert correlations work best along with a Reynolds Analogy Factor of ≈ 1.2. Statistics from the mean and fluctuating turbulent flow fields are briefly discussed. The hope is that the DNS database generated will be useful for physics based improvements of RANS and LES models.

AB - We perform direct numerical simulations (DNS) of transition to turbulence in a hypersonic boundary layer flow. The flow conditions correspond to a Mach 6, cold-wall flow with a wall temperature to adiabatic temperature ratio (Tw/Taw) of around 0.16. Themomentum thickness Reynolds number Reθ goes up to around 6000 at the end of the computed turbulent zone. Comparisons are made to empirical skin-friction and heat transfer coefficients. We find that the Van Driest II and Eckert correlations work best along with a Reynolds Analogy Factor of ≈ 1.2. Statistics from the mean and fluctuating turbulent flow fields are briefly discussed. The hope is that the DNS database generated will be useful for physics based improvements of RANS and LES models.

UR - https://www.scopus.com/pages/publications/85088720907

UR - https://www.scopus.com/pages/publications/85088720907#tab=citedBy

U2 - 10.2514/6.2011-3564

DO - 10.2514/6.2011-3564

M3 - Conference contribution

AN - SCOPUS:85088720907

SN - 9781600869471

T3 - 41st AIAA Fluid Dynamics Conference and Exhibit

BT - 41st AIAA Fluid Dynamics Conference and Exhibit

PB - American Institute of Aeronautics and Astronautics Inc.

T2 - 41st AIAA Fluid Dynamics Conference and Exhibit 2011

Y2 - 27 June 2011 through 30 June 2011

ER -

DNS of transition to turbulence in a hypersonic boundary layer

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