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TECHNICAL PAPERS

Modeling of Laminar-Turbulent Transition for High Freestream Turbulence

[+] Author and Article Information
J. Steelant

European Space Research and Technology Centre, Aerothermodynamics Section, Noordwijk, The Netherlands

E. Dick

Department of Flow, Heat and Combustion, University of Gent, Gent, Belgium

J. Fluids Eng 123(1), 22-30 (Oct 13, 2000) (9 pages) doi:10.1115/1.1340623 History: Received June 26, 2000; Revised October 13, 2000
Copyright © 2001 by ASME
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References

Figures

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Velocity distribution for T3C1
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Geometry with location of the different blocks: C-grid around turbine blade, H-grid along the outlet angle
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Evolution of τ along the wall for T3A compared with experimental γ values
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Normal variation of τ prior to the transition point for T3A compared with the suggested free stream factor
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Evolution of τ along the wall for T3C1
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Skin friction coefficient for T3A (top) and T3C1 (bottom)
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Shape factor for T3A (top) and T3C1 (bottom)
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u′2˜/Ue for T3A at Rex=169200 (top), Rex=238400 (middle) and at Rex=344700 (bottom)
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Heat transfer distribution for MUR239 (Tui=6 percent); full line: calculated heat transfer, dashed line: intermittency (× 1000), symbols: experiments (other Tui also shown)
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Isentropic Mach number distribution for MUR239; full line: calculated, symbols: experiment
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Heat transfer distribution for MUR245 (Tui=4 percent); full line: calculated heat transfer, dashed line: intermittency (× 1000), symbols: experiments (other Tui also shown)
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Isentropic Mach number distribution for MUR245; full line: calculated, symbols: experiment
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Isentropic Mach number distribution for MUR241; full line: calculated, symbols: experiments
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Heat transfer distribution for MUR241 (legend see Fig. 9)

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