scholarly journals Prediction of Reynolds stresses in high-Mach-number turbulent boundary layers using physics-informed machine learning

2018 ◽  
Vol 33 (1) ◽  
pp. 1-19 ◽  
Author(s):  
Jian-Xun Wang ◽  
Junji Huang ◽  
Lian Duan ◽  
Heng Xiao
Keyword(s):  
Machine Learning ◽  
Mach Number ◽  
Boundary Layers ◽  
Turbulent Boundary Layers ◽  
Reynolds Stresses ◽  
High Mach Number ◽  
High Mach

An unseeded air MHD accelerator concept for high Mach number hypersonic propulsion testing

1989 ◽  
Author(s):  
GLOYD SIMMONS ◽  
GORDON NELSON ◽  
ROBERT HIERS ◽  
ARTHURB. WESTERN
Keyword(s):  
Mach Number ◽  
Hypersonic Propulsion ◽  
High Mach Number ◽  
High Mach

Microinstabilities associated with a high Mach number, perpendicular bow shock

1984 ◽  
Vol 37 (1-2) ◽  
Author(s):  
C.S. Wu ◽  
D. Winske ◽  
Y.M. Zhou ◽  
S.T. Tsai ◽  
P. Rodriguez ◽  
...  
Keyword(s):  
Mach Number ◽  
Bow Shock ◽  
High Mach Number ◽  
High Mach

Interaction of high Mach-number shocks in laser-produced plasmas

2013 ◽  
Vol 9 (1) ◽  
pp. 187-191 ◽  
Author(s):  
T. Morita ◽  
Y. Sakawa ◽  
Y. Kuramitsu ◽  
S. Dono ◽  
H. Tanji ◽  
...  
Keyword(s):  
Mach Number ◽  
High Mach Number ◽  
High Mach

Modeling of External Pressure Gradient Influence on the Stability of Disturbances in the Boundary Layers of Compressed Gas

2013 ◽  
Vol 8 (4) ◽  
pp. 64-75
Author(s):  
Sergey Gaponov ◽  
Natalya Terekhova
Keyword(s):  
Mach Number ◽  
Pressure Gradient ◽  
Boundary Layers ◽  
Leading Edge ◽  
External Pressure ◽  
Transition To Turbulence ◽  
Compressed Gas ◽  
High Mach ◽  
The Stability ◽  
Very High

This work continues the research on modeling of passive methods of management of flow regimes in the boundary layers of compressed gas. Authors consider the influence of pressure gradient on the evolution of perturbations of different nature. For low Mach number M = 2 increase in pressure contributes to an earlier transition of laminar to turbulent flow, and, on the contrary, drop in the pressure leads to a prolongation of the transition to turbulence. For high Mach number M = 5.35 found that the acoustic disturbances exhibit a very high dependence on the sign and magnitude of the external gradient, with a favorable gradient of the critical Reynolds number becomes smaller than the vortex disturbances, and at worst – boundary layer is destabilized directly on the leading edge

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