Special Section Articles

Partially-Averaged Navier–Stokes Simulations of High-Speed Mixing Environment

[+] Author and Article Information
Ravichandra Srinivasan

Research Associate
Department of Aerospace Engineering,
Texas A&M University,
College Station, TX 77843
e-mail: rsrinivasan@tamu.edu

Sharath S. Girimaji

Department of Aerospace Engineering,
Texas A&M University,
College Station, TX 77843
e-mail: girimaji@tamu.edu

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received December 18, 2012; final manuscript received December 8, 2013; published online April 28, 2014. Assoc. Editor: Ye Zhou.

J. Fluids Eng 136(6), 060903 (Apr 28, 2014) (8 pages) Paper No: FE-12-1641; doi: 10.1115/1.4026234 History: Received December 18, 2012; Revised December 08, 2013

Accurate simulation of the fuel-air mixing environment is crucial for high-fidelity scramjet calculations. We compute the velocity fields of jet into supersonic freestream flow and cavity flow typical of scramjet flame-holding applications at different scale resolutions using the partially-averaged Navier–Stokes (PANS) method. We present a sequence of variable resolution computations to demonstrate the potential of PANS method for high-speed mixing environment calculations.

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Fig. 1

Subsonic backward-facing step. Recovery of the prespecified level of viscosity reduction.

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Fig. 2

Subsonic backward-facing step. Length scale distribution at different fks. DNS data from decaying isotropic turbulence also shown for comparison.

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Fig. 3

Cavity flow: centerline mean velocity profiles, zero-transport model, clustered grid. RANS, LES, and PANS comparison against experimental data.

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Fig. 4

Unsteady RANS and PANS vorticity contours

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Fig. 5

Mach 5 case: Pitot pressure comparison of experimental and DES results at z/deff=8.0. The left half of the image corresponds to simulation results and the right half is from experiments.

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Fig. 6

Mach 5 case: Line plot at z/deff=8.0 for pitot pressure for RANS, DES, and experimental results

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Fig. 7

Mach 5 case: DES and PANS simulations of jet in cross-stream

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Fig. 8

Mach 5 case: Observed flow structures in experiments, DES, and PANS simulations. (a) Injector seed particles show eddy structures in the shear layer (Bowersox, Fan, and Lee [14]). (b) Transient DES results do not resolve these eddies. (c) Eddy formation observed in PANS with fk=0.35. (d) More resolved eddies seen in PANS results with fk=0.20.

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Fig. 9

Mach 2 case: DES and PANS simulations of jet in cross-stream

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Fig. 10

Mach 2 case: Observed flow structures in experiments, DES, and PANS simulations. (a) NO PLIF image shows eddy structures in the shear layer [18]. (b) DES results show corresponding eddy structure. (c) PANS with fk=0.35 does not resolve these structures. (d) PANS with fk=0.20 is comparable to DES in the shear layer.



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