Direct numerical simulation of supersonic turbulent boundary layer over a compression ramp
M Wu, MP Martin - AIAA journal, 2007 - arc.aiaa.org
MANY aspects of shock wave and turbulent boundary layer interaction (STBLI) are not fully
understood, including the dynamics of shock unsteadiness, turbulence amplification and …
understood, including the dynamics of shock unsteadiness, turbulence amplification and …
Large-eddy simulation of shock-wave/turbulent-boundary-layer interaction
MS Loginov, NA Adams… - Journal of Fluid …, 2006 - cambridge.org
Well-resolved large-eddy simulations (LES) are performed in order to investigate flow
phenomena and turbulence structure of the boundary layer along a supersonic compression …
phenomena and turbulence structure of the boundary layer along a supersonic compression …
Numerical simulations of shock/boundary layer interactions using time-dependent modeling techniques: A survey of recent results
JR Edwards - Progress in Aerospace Sciences, 2008 - Elsevier
Supersonic or hypersonic flows within and around flight vehicles inevitably involve
interactions of strong shock waves with boundary layers. Flows within inlet/isolator …
interactions of strong shock waves with boundary layers. Flows within inlet/isolator …
Response of a panel to shock impingement: Modeling and comparison with experiments-part 2
This paper describes an on-going effort towards the prediction of structural responses to
shock impingements. This work is an extension of a previous effort, where the focus is on …
shock impingements. This work is an extension of a previous effort, where the focus is on …
[HTML][HTML] Characteristics of reattached boundary layer in shock wave and turbulent boundary layer interaction
T Fulin, D Junyi, LI Xinliang - Chinese Journal of Aeronautics, 2022 - Elsevier
The reattached boundary layer in the interaction of an oblique shock wave with a flat-plate
turbulent boundary layer at Mach number 2.25 is studied by means of Direct Numerical …
turbulent boundary layer at Mach number 2.25 is studied by means of Direct Numerical …
Robust and efficient treatment of temperature feedback in fluid–thermal–structural analysis
AR Crowell, BA Miller, JJ McNamara - AIAA Journal, 2014 - arc.aiaa.org
One of the primary challenges in the development of high-speed systems is accurate and
efficient prediction of the aerodynamic heating, particularly for lightweight systems where …
efficient prediction of the aerodynamic heating, particularly for lightweight systems where …
Gas-kinetic schemes for direct numerical simulations of compressible homogeneous turbulence
W Liao, Y Peng, LS Luo - Physical Review E—Statistical, Nonlinear, and Soft …, 2009 - APS
We apply the gas-kinetic scheme (GKS) for the direct numerical simulations (DNSs) of
compressible decaying homogeneous isotropic turbulence (DHIT). We intend to study the …
compressible decaying homogeneous isotropic turbulence (DHIT). We intend to study the …
Numerical analysis of shock wave and supersonic turbulent boundary interaction between adiabatic and cold walls
F Tong, Z Tang, C Yu, X Zhu, X Li - Journal of Turbulence, 2017 - Taylor & Francis
Direct numerical simulations of shock wave and supersonic turbulent boundary layer
interaction in a 24° compression ramp with adiabatic and cold-wall temperatures are …
interaction in a 24° compression ramp with adiabatic and cold-wall temperatures are …
Measurement of flow perturbation spectra in mach 4.5 corner separation zone
B Hedlund, A Houpt, S Gordeyev, S Leonov - AIAA Journal, 2018 - arc.aiaa.org
Characterization of the M= 4.5 flow over a flat-plate model with a 30 deg compression ramp
was performed with low-enthalpy (T 0= 300 K) and high-enthalpy (T 0= 800–1250 K) flow …
was performed with low-enthalpy (T 0= 300 K) and high-enthalpy (T 0= 800–1250 K) flow …
Flow visualization of Mach 3 compression ramp with different upstream boundary layers
Y Wu, S Yi, L He, Z Chen, Y Zhu - Journal of Visualization, 2015 - Springer
Experimental studies of supersonic flow over several compression ramps are carried out in a
Mach 3.0 wind tunnel; the upstream boundary layers include laminar flow, transitional flow …
Mach 3.0 wind tunnel; the upstream boundary layers include laminar flow, transitional flow …