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REVIEW ARTICLES

Burnett equations for simulation of transitional flows

[+] Author and Article Information
Ramesh K Agarwal

Aerospace Research and Engineering Center, Washington University, St Louis MO 63130rka@me.wustl.edu

Keon-Young Yun

National Institute for Aviation Research, Wichita State University, Wichita KS 67260-0093 keon-young.yun@wichita.edu

Appl. Mech. Rev 55(3), 219-240 (Jun 10, 2002) (22 pages) doi:10.1115/1.1459080 History: Online June 10, 2002
Copyright © 2002 by ASME
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References

Figures

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Characteristic trajectories of the 1D Navier-Stokes equations
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Characteristic trajectories of the 1D conventional Burnett equations; Euler equations are used to express the material derivatives D()/Dt in terms of spatial derivatives.
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Characteristic trajectories of the 1D augmented Burnett equations; Euler equations are used to express the material derivatives D()/Dt in terms of spatial derivatives.
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Characteristic trajectories of the 1D super-Burnett equations; Euler equations are used to express the material derivatives D()/Dt in terms of spatial derivatives.
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Plot showing the variation of reciprocal density thickness with Mach number, obtained with the Navier-Stokes, Woods, Simplified Woods 49, and Burnett equations for a hard sphere gas 22. Experimental data was obtained from Alsemeyer 50.
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2D computational grid (50×82 mesh) around a blunt body, rn=0.02 m
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Density distributions along the stagnation streamline for blunt body flow: Air, M=10, and Kn=0.1
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Velocity distributions along the stagnation streamline for blunt body flow: Air, M=10, and Kn=0.1
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Temperature distributions along the stagnation streamline for blunt body flow: Air, M=10, and Kn=0.1
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Comparison of temperature contours for blunt body flow: Air, M=10, and Kn=0.1
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Comparison of Mach number contours for blunt body flow: Air, M=10, and Kn=0.1
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Density distributions along the stagnation streamline for a hemispherical nose: Argon, M=10.95, and Kn=0.2
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Temperature distributions along the stagnation streamline for a hemispherical nose: Argon, M=10.95, and Kn=0.2
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Density distributions along the stagnation streamline for a hemispherical nose: Hard-sphere gas, M=10, and Kn=0.1
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Temperature distribution along the stagnation streamline for a hemispherical nose: Hard-sphere gas, M=10, and Kn=0.1
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Density distributions along the stagnation streamline for a hemispherical nose at an angle of attack: Air, M=10, and Kn=0.1768
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Temperature distributions along the stagnation streamline for a hemispherical nose at an angle of attack: Air, M=10, and Kn=0.1768
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Side view of the grid (61×100 mesh) around a hyperboloid nose of radius rn=1.362 m
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Density distributions along the stagnation streamline for a hyperboloid nose: Air, M=25.3, and Kn=0.227
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Temperature distributions along the stagnation streamline for a hyperboloid nose: Air, M=25.3, and Kn=0.227
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Density distributions along the stagnation streamline for a hyperboloid at an angle of attack: Air, M=25.3, and Kn=0.227
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Temperature distributions along the stagnation streamline for a hyperboloid at an angle of attack: Air, M=25.3, and Kn=0.227
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Comparison of temperature contours for a hyperboloid at an angle of attack: Air, M=25.3,Kn=0.227, and α=15° (front view of exit plane)
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Grid (101×91 mesh) around a NACA 0012 airfoil, c=0.04 m
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Density contours for NACA 0012 airfoil: Air, M=0.8, and Kn=0.014
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Pressure distributions along NACA 0012 airfoil surface: Air, M=0.8, and Kn=0.014
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Slip velocity distributions along NACA 0012 airfoil surface: Air, M=0.8, and Kn=0.014
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Comparison of velocity profiles at various streamwise locations: Knin=0.088,Knout=0.2, and Pin/Pout=2.28    
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Comparison of mass flow rates along the microchannel: Knin=0.088,Knout=0.2, and Pin/Pout=2.28
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Comparison of pressure distribution along the centerline: Knin=0.088,Knout=0.2, and Pin/Pout=2.28
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Comparison of streamwise velocity distributions along the centerline: Knin=0.088,Knout=0.2, and Pin/Pout=2.28
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Comparison of slip velocity distributions along the wall: Knin=0.088,Knout=0.2, and Pin/Pout=2.28
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Microchannel geometry and grid
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Comparisons of contours between Navier-Stokes and augmented Burnett equations: Helium, M=5, and Kn=0.7
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Comparisons of density, temperature, pressure, and Mach number profiles along the centerline of the channel: Helium, M=5, and Kn=0.07
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Comparisons of density, temperature, pressure, and Mach number profiles along the wall of the channel: Helium, M=5, and Kn=0.07
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Comparisons of temperature profiles across the channel at various locations: Helium, M=5, and Kn=0.07
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Comparisons of velocity profiles across the channel at various locations: Helium, M=5, and Kn=0.07

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