Vortex Breakdown Stimulation By The Steady And Periodic Pulse Energy Deposition In A Vicinity of Shock Wave

Author(s):  
A. Zheltovodov ◽  
E. Pimonov ◽  
D. Knight
Shock Waves ◽  
2012 ◽  
Vol 22 (6) ◽  
pp. 521-531 ◽  
Author(s):  
N. Ohnishi ◽  
M. Tate ◽  
Y. Ogino

Shock Waves ◽  
2006 ◽  
Vol 15 (5) ◽  
pp. 353-362 ◽  
Author(s):  
D. V. Khotyanovsky ◽  
A. N. Kudryavtsev ◽  
M. S. Ivanov

Materials ◽  
2021 ◽  
Vol 14 (13) ◽  
pp. 3553
Author(s):  
Dengwang Wang ◽  
Yong Gao ◽  
Sheng Wang ◽  
Jie Wang ◽  
Haipeng Li

Carbon/Phenolic (C/P), a typical anisotropic material, is an important component of aerospace and often used to protect the thermodynamic effects of strong X-ray radiation. In this paper, we establish the anisotropic elastic-plastic constitutive model, which is embedded in the in-house code “RAMA” to simulate a two-dimensional thermal shock wave induced by X-ray. Then, we compare the numerical simulation results with the thermal shock wave stress generated by the same strong current electron beam via experiment to verify the correctness of the numerical simulation. Subsequently, we discuss and analyze the rules of thermal shock wave propagation in C/P material by further numerical simulation. The results reveal that the thermal shock wave represents different shapes and mechanisms by the radiation of 1 keV and 3 keV X-rays. The vaporization recoil phenomenon appears as a compression wave under 1 keV X-ray irradiation, and X-ray penetration is caused by thermal deformation under 3 keV X-ray irradiation. The thermal shock wave propagation exhibits two-dimensional characteristics, the energy deposition of 1 keV and 3 keV both decays exponentially, the energy deposition of 1 keV-peak soft X-ray is high, and the deposition depth is shallow, while the energy deposition of 3 keV-peak hard X-ray is low, and the deposition depth is deep. RAMA can successfully realize two-dimensional orthotropic elastoplastic constitutive relation, the corresponding program was designed and checked, and the calculation results for inspection are consistent with the theory. This study has great significance in the evaluation of anisotropic material protection under the radiation of intense X-rays.


2007 ◽  
Vol 33 (7) ◽  
pp. 575-577 ◽  
Author(s):  
I. A. Znamenskaya ◽  
I. V. Mursenkova ◽  
D. M. Orlov ◽  
N. N. Sysoev

2014 ◽  
Vol 26 (9) ◽  
pp. 096103 ◽  
Author(s):  
T. Osuka ◽  
E. Erdem ◽  
N. Hasegawa ◽  
R. Majima ◽  
T. Tamba ◽  
...  

2010 ◽  
Vol 654 ◽  
pp. 387-416
Author(s):  
SHANKAR GHOSH ◽  
KRISHNAN MAHESH

The interaction of a laser-induced plasma with isotropic turbulence is studied using numerical simulations. The simulations use air as the working fluid and assume local thermodynamic equilibrium. The numerical method is fully spectral and uses a shock-capturing scheme in a corrector step. A model problem involving the effect of energy deposition on an isolated vortex is studied as a first step towards plasma/turbulence interaction. Turbulent Reynolds number Reλ = 30 and fluctuation Mach numbers Mt = 0.001 and 0.3 are considered. A tear-drop-shaped shock wave is observed to propagate into the background, and progressively become spherical in time. The turbulence experiences strong compression due to the shock wave and strong expansion in the core. This behaviour is spatially inhomogeneous and non-stationary in time. Statistics are computed as functions of radial distance from the plasma axis and angular distance across the surface of the shock wave. For Mt = 0.001, the shock wave propagates on a much faster time scale compared to the turbulence evolution. At Mt of 0.3, the time scale of the shock wave is comparable to that of the background. For both cases the mean flow is classified into shock formation, shock propagation and subsequent collapse of the plasma core, and the effect of turbulence on each of these phases is studied in detail. The effect of mean vorticity production on the turbulent vorticity field is also discussed. Turbulent kinetic energy budgets are presented to explain the mechanism underlying the transfer of energy between the mean flow and background turbulence.


The objective of this paper was to analysis the condition for the appearance of the many types of interaction of a vortex core with shock wave over a flapped wing of a supersonic aircraft. A five digit NACA 23012 aerofoil was selected for this work. Structured Mesh was generated by Quadrilaterals Method. Steady-state density based implicit solver and K-ω SST turbulent model was selected. Q criterion method with vorticity magnitude was used to calculate the vortex core. NACA aerofoil Scaled model was manufactured by using NACA profile for experimental work and CFD results were validated by pressure coefficient calculated by wind tunnel setup. Finally, concluded that weak interaction with no vortex breakdown was observed at M= 1.4 and a strong interaction with a bubble-like vortex breakdown formed at M= 1.8 and It found that when a shock wave interact with vortex core, disturbance is generated, which expands along the shock wave and deformed into many small vortices. The flow field is compressed behind the curved shock wave which is reason of acoustic waves. This principle are related to the shock–turbulence interaction which is one of major source of noise. Also concluded that initially at low angle of attack,it observed a strong organized flow field in the downstream region which is due to less strength of the shock. The development of a transmitted shock wave across the vortex core was observed because of shock scattering phenomenon. The moderate breakdown of the vorticity field that occurs after a very strong shock at M =1.4 also observed and the breakdown was more intense when increased Mach No. up to 1.8. Weak and strong interaction region were observed and three stages of interaction found by the flow field over aerofoil at high Mach No. =1.8.


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