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VULCAN APPLICATION PORTFOLIO
Aerodynamics, Aerothermodynamics, and Acoustics Competency Logo


Hypersonic Airbreathing Propulsion Branch
Hypersonic Airbreathing Propulsion Branch


The following is a sample of pertinent VULCAN applications :

Laminar simulation of Mach 6.0 flow over a 7.5 degree compression corner2-D, Laminar simulation of Mach 6.0 flow over a 7.5 degree compression corner. The computation was performed by Charles E. Cockrell, Jr. of NASA Langely Research Center (LaRC) HAPB using:
Laminar, calorically perfect gas with gamma = 1.4
Roe's flux difference splitting using MUSCL kappa=1/3 scheme and
Venkatakrishnan's smooth limiter

Available images:
1) Computed Mach number contours (32 kbytes)
2) Computed wall pressure distribution vs. experimental data (40 kbytes)
3) Computed wall skin friction distribution vs. experimental data (42 kbytes)

2-D simulation of the HAPB Direct Connect Supersonic Combustion Test Facility Nozzle2-D, turbulent, vitiated air simulation of the HAPB Direct Connect Supersonic Combustion Test Facility Nozzle. The computation and experiment were performed by Ron Springer of George Washington University using:
Menter k-omega turbulence model and Wilcox wall matching functions
Low dissipation flux splitting scheme using MUSCL kappa=1/3 scheme
and Venkatakrishnan's smooth limiter

Available images:
1) Computed nozzle Mach contours (57 kbytes)
2) Computed pitot pressure profile vs. measured profile at nozzle exit (33 kbytes)

2-D simulation of an aerospike nozzle2-D, turbulent, calorically perfect air simulation of an aerospike nozzle operating at a nozzle pressure ratio of 45.4. The computation was performed by Jeff Lin of NASA Marshall Space Flight Center using:
Wilcox (98) k-omega turbulence model
Roe's flux difference split scheme using MUSCL kappa=1/3 scheme and vanLeer's limiter

Available images:
1) Computed nozzle density gradient contours (14 kbytes)
2) Computed wall pressure distribution vs. measured wall pressure distribution (42 kbytes)

2-D simulation of Mach 3.0 flow over a ramped cavity2-D, turbulent simulation of Mach 3.0 flow over the ramped cavity experiment of G. Settles using:
Wilcox (98) k-omega turbulence model and Wilcox wall matching functions
Low dissipation flux splitting scheme using MUSCL kappa=1/3 scheme and Venkatakrishnan's smooth limiter

Available images:
3-D simulation of Mach 1.0 round jet injected normal to a Mach 3.0 turbulent boundary layer3-D, turbulent simulation of Mach 1.0 thermally perfect turbulent air round jet injected normal to a Mach 3.0 thermally perfect air turbulent boundary layer. The computation was performed by Dr. Rob Baurle of Taitech, Inc. at WPAFB for the HyTech program using:
Menter SST k-omega turbulence model and Wilcox wall matching functions
Low dissipation flux splitting scheme using MUSCL kappa=1/3 scheme and
vanLeer's limiter

Available images:
1) Computed Mach Contours on the jet center-line plane (76 kbytes)
2) Computed wall pressure contours vs. xperimental data from pressure sensitive paint (652 kbytes)
3) Experimental PLIF images (left) vs. computed injectant gas contours (right) at two axial cuts through jet plume (35 kbytes)

3-D simulation of mixing for a ramjet strut fuel injector3-D, turbulent simulation of the injection of a helium air mixture into air for a scramjet fuel injection mixing experiments run at WPAFB. The computations were performed by Dr. Rob Baurle of Taitech, Inc. at WPAFB using:
Menter k-omega turbulence model and Wilcox wall matching functions
Roe's flux difference split scheme using MUSCL kappa=1/3 scheme and vanLeer's limiter

Available images:
3-D simulation of dual-mode, hydrocarbon fueled, scramjet combustor3-D, turbulent simulation of a hydrocarbon-fueled scramjet combustor experiment run in test cell 22 at WPAFB. The scramjet was simulated for operation at dual-mode conditions. The computation was performed by Dr. Rob Baurle of Taitech, Inc. at WPAFB for the HyTech program using:
Menter k-omega turbulence model and Wilcox wall matching functions
Low dissipation flux splitting scheme using MUSCL kappa=1/3 scheme and vanLeer's limiter
Six species, three-step ethylene reduced kinetic model

Available images:
Axi-symmetric, turbulent, time accurate simulation of a single wall carbon nanotube(SWNT) production  experimentAxi-symmetric, turbulent, time accurate simulation of a single wall carbon nanotube (SWNT) production experiment conducted in the laser ablation oven facility at NASA Johnson Space Center. The computation was performed by Dr. Robert Greendyke, of the Department of Mechanical Engineering of the University of Texas at Tyler while at NASA JSC as a NASA/ASEE Summer Faculty Fellow, using:
Wilcox (98) k-omega turbulence model
Roe's flux difference split scheme using MUSCL kappa=1/3 scheme and minmod limiter
Two species (Ar and C3) frozen flow

Available images:
1) Computed C3 mass fraction contours (40 kbytes)
2) Computed static pressure contours (42 kbytes)

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NASA Official Responsible For Content: Robert A. Baurle

This site's most recent update took place: 11/15/2010

Site Curator: Robert A. Baurle  (Robert.A.Baurle@nasa.gov)

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