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Hypersonic nonequilibrium flow over the STS-2 space shuttle orbitor
Hypersonic nonequilibrium flow over the STS-2 space shuttle orbitor
Two-temperature five-species model
H = 54.8 km, M = 12.86, α = 39.4°
Hypersonic nonequilibrium flow over the AS-202 command module
Hypersonic nonequilibrium flow over the AS-202 command module
Two-temperature five-species model
t = 4510 s, H = 66 km, M = 25.6, α = 17.8°
Hypersonic nonequilibrium flow over the Mars Pathfinder
Hypersonic nonequilibrium flow over the Mars Pathfinder
Two-temperature five-species (C, O, O2, CO, CO2) model
Hypersonic nonequilibrium flow over a double cone
Hypersonic nonequilibrium flow over a double cone
Two-temperature five-species model
Mack's second mode in a hypersonic boundary layer
Mack's second mode in a hypersonic boundary layer
Linear evolution excited by a wall blowing suction actuator
DNS of a supersonic turbulent boundary layer
DNS of a supersonic turbulent boundary layer
Bypass transition triggered by wall blowing suction
Global stability analysis
Global stability analysis
Global modes in hypersonic flow over a double cone (run 35 conducted at CUBRC)
Three-dimensionality induced by intrinsic instability over a double cone
Three-dimensionality induced by intrinsic instability over a double cone
DNS with no external disturbances
Run 35 conducted at CUBRC
The saturated flow is three-dimensional and unsteady.
Scramjet engine combustor
Scramjet engine combustor
Inviscid wedge-induced oblique detonation wave
Inviscid wedge-induced oblique detonation wave
One-step model
Q = 50, Ea = 50, γ = 1.2, M = 12.5, θ = 26°
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