Optimal regular reflection of oblique shocks

2019 ◽  
Vol 163 ◽  
pp. 225-231 ◽  
Author(s):  
M.V. Chernyshov ◽  
O.A. Tolpegin
2014 ◽  
Vol 1061-1062 ◽  
pp. 1096-1099
Author(s):  
Jian Lin Zhong ◽  
Gui Gao Le

The mathematic express of positive scheme axis-symmetric Euler equations is derived. With the numerical calculation of oblique shocks regular reflection problem, the validity of the positive scheme method and the self-programmed codes is verified. The positive scheme method is developed to solve the axis-symmetric Euler equations and then used to simulate the supersonic axis-symmetric flow over missile afterbody. The results show that: the numerical simulation match well with the experimental results and the numerical results obtained by the already existing high accuracy scheme method, the correctness of the development of positive scheme method is verified.


2004 ◽  
Vol 42 (6) ◽  
pp. 911-918 ◽  
Author(s):  
T. V. Bazhenova ◽  
V. V. Golub ◽  
A. L. Kotel?nikov ◽  
A. S. Chizhikov ◽  
M. V. Bragin ◽  
...  

AIAA Journal ◽  
2020 ◽  
Vol 58 (11) ◽  
pp. AU4-AU4
Author(s):  
Daniel Martínez-Ruiz ◽  
Cesar Huete ◽  
Antonio L. Sánchez ◽  
Forman A. Williams

2014 ◽  
Vol 6 (3) ◽  
pp. 93-110 ◽  
Author(s):  
Mohd Ali ◽  
Farrukh Alvi ◽  
Rajan Kumar ◽  
Kareem Ahmed

2008 ◽  
Vol 599 ◽  
pp. 81-110 ◽  
Author(s):  
C. J. WANG ◽  
S. L. XU ◽  
C. M. GUO

Gaseous detonation propagation in a bifurcated tube was experimentally and numerically studied for stoichiometric hydrogen and oxygen mixtures diluted with argon. Pressure detection, smoked foil recording and schlieren visualization were used in the experiments. Numerical simulation was carried out at low initial pressure (8.00kPa), based on the reactive Navier–Stokes equations in conjunction with a detailed chemical reaction model. The results show that the detonation wave is strongly disturbed by the wall geometry of the bifurcated tube and undergoes a successive process of attenuation, failure, re-initiation and the transition from regular reflection to Mach reflection. Detonation failure is attributed to the rarefaction waves from the left-hand corner by decoupling leading shock and reaction zones. Re-initiation is induced by the inert leading shock reflection on the right-hand wall in the vertical branch. The branched wall geometry has only a local effect on the detonation propagation. In the horizontal branch, the disturbed detonation wave recovers to a self-sustaining one earlier than that in the vertical branch. A critical case was found in the experiments where the disturbed detonation wave can be recovered to be self-sustaining downstream of the horizontal branch, but fails in the vertical branch, as the initial pressure drops to 2.00kPa. Numerical simulation also shows that complex vortex structures can be observed during detonation diffraction. The reflected shock breaks the vortices into pieces and its interaction with the unreacted recirculation region induces an embedded jet. In the vertical branch, owing to the strength difference at any point and the effect of chemical reactions, the Mach stem cannot be approximated as an arc. This is different from the case in non-reactive steady flow. Generally, numerical simulation qualitatively reproduces detonation attenuation, failure, re-initiation and the transition from regular reflection to Mach reflection observed in experiments.


Fluids ◽  
2021 ◽  
Vol 6 (9) ◽  
pp. 315
Author(s):  
Pavel Bulat ◽  
Konstantin Volkov ◽  
Igor Volobuev

In this paper, we study the intersection (interaction) between several steady shocks traveling in the same direction. The interaction between overtaking shocks may be regular or irregular. In the case of regular reflection, the intersection of overtaking shocks leads to the formation of a resulting shock, contact discontinuity, and some reflected discontinuities. The type of discontinuity depends on the parameters of incoming shocks. At the irregular reflection, a Mach shock forms between incoming overtaking shocks. Reflected discontinuities come from the points of intersection of the Mach stem with the incoming shocks. We also consider the possible types of shockwave configurations that form both at regular and irregular interactions of several overtaking shocks. The regions of existence of overtaking shock waves with different types of reflected shock and the intensity of reflected shocks are defined. The results obtained in the study can potentially be useful for designing supersonic intakes and advanced jet engines.


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