Investigation of the flow field developed behind a planar shock wave propagating into a reactive gas solid suspension

KSME Journal ◽  
1990 ◽  
Vol 4 (2) ◽  
pp. 167-171 ◽  
Author(s):  
M. Olim ◽  
G. Ben-Dor ◽  
M. Mond ◽  
O. Igra
Keyword(s):  
Shock Wave ◽  
Flow Field ◽  
Planar Shock ◽  
Solid Suspension ◽  
Planar Shock Wave ◽  
Reactive Gas

Application of a High-Resolution Compact Finite Difference Method to Computational Aeroacoustics of Compressible Flows

2011 ◽  
Author(s):  
Zhifeng Zuo ◽  
Hiroshi Maekawa
Keyword(s):  
Shock Wave ◽  
High Resolution ◽  
Flow Field ◽  
Acoustic Wave ◽  
Acoustic Waves ◽  
Compressible Flows ◽  
Compact Finite Difference Method ◽  
Reflected Shock ◽  
Planar Shock ◽  
Planar Shock Wave

WCNS is an efficient high-resolution nonlinear scheme for solving flow-fields including discontinuity. In the present paper, a two-dimensional, unsteady, compressible flow field produced by the interaction between a strong planar shock wave and a strong vortex are simulated numerically using WCNS. The simulation shows the effects of the vortex on a planar shock and the production of acoustic waves by the shock-vortex interaction. At the early times of interaction, the shock wave is perturbed by the vortex and a precursor is produced; with the shock wave emerges from the vortex flow field, a Mach structure was generated and the secondary acoustic wave was formed by the interaction of the reflected shock (MR2) with the precursor. Both components of acoustic wave (the precursor and the second sound wave) propagate radially and have a quadrupolar nature. By this simulation, the ability of WCNS for computational aeroacoustic problems is confirmed.

scholarly journals Planar shock wave sliding over a water layer

2016 ◽  
Vol 57 (8) ◽  
Author(s):  
V. Rodriguez ◽  
G. Jourdan ◽  
A. Marty ◽  
A. Allou ◽  
J.-D. Parisse
Keyword(s):  
Shock Wave ◽  
Water Layer ◽  
Planar Shock ◽  
Planar Shock Wave

Flow of a planar shock wave around a thermal layer at a rigid wall

1991 ◽  
Vol 31 (3) ◽  
pp. 354-361
Author(s):  
B. I. Zaslavskii ◽  
S. Yu. Morozkin ◽  
A. A. Prokof'ev ◽  
V. R. Shlegel'
Keyword(s):  
Shock Wave ◽  
Rigid Wall ◽  
Planar Shock ◽  
Planar Shock Wave ◽  
Thermal Layer

Specifics of generating explosively formed projectiles of variable shape from metal liners

2019 ◽  
Author(s):  
P.V. Kruglov ◽  
V.I. Kolpakov ◽  
I.A. Bolotina
Keyword(s):  
Shock Wave ◽  
Aspect Ratio ◽  
Detonation Wave ◽  
Variable Shape ◽  
Internal Surfaces ◽  
Planar Shock ◽  
Wave Generator ◽  
Planar Shock Wave ◽  
Metal Liner ◽  
A Charge

We propose using charges generating explosively formed projectiles of variable shape to remotely demolish structurally unsound concrete or brick walls of buildings and other structures. The paper considers the charges required, their design and operation. The operation of such a charge involves the explosive material accelerating a metal liner, covering a distance of up to several hundred charge diameters. The metal liner deforms while moving and assumes a compact shape. We used variable thickness copper liners, the external and internal surfaces of which are formed by a combination of spherical surfaces. A planar shock wave generator featuring a variable detonation wave slope is considered as the initiation system for the charge. We present the results of numerically simulating our explosive charge operation in order to determine how charge parameters affect performance. We estimated charge performance via two projectile parameters: its shape and velocity. The study also evaluated the effect of the planar shock wave generator slope on the projectile shape. We obtained projectile velocity and aspect ratio as functions of the slope of the converging detonation wave. We determined that decreasing the slope of the converging detonation wave front leads to an increase in the aspect ratio and velocity of the explosively formed projectile.

EXPERIMENTAL AND NUMERICAL INVESTIGATION OF HYPERSONIC JAWS INLET

2010 ◽  
Vol 24 (13) ◽  
pp. 1409-1412 ◽  
Author(s):  
HAO DONG ◽  
CHENG-PENG WANG ◽  
KE-MING CHENG
Keyword(s):  
Boundary Layer ◽  
Flow Field ◽  
Static Pressure ◽  
Free Stream ◽  
Flow Coefficient ◽  
Plane Symmetric ◽  
Pressure Distributions ◽  
Planar Shock ◽  
Flow Field Characteristics ◽  
Planar Shock Wave

In order to obtain the flow field characteristics and the influence of boundary layer, numerical simulations and wind tunnel tests are conducted for two streamline traced Jaws inlets at Mach number 7. The inlets are designed based on a flow field with 8-7 planar shock wave (the ramp in pitch plane is inclined at 8° to the free stream and in yaw plane is inclined at 7° to the free stream, yielding planar shocks). In the study, the static pressure distributions were measured and analyzed along the plane-symmetric centerline of the inlet with and without the boundary layer correction, respectively. Results show that boundary layer correction can obviously weaken the viscous influence to the inlet, increasing the mass flow coefficient and improving total pressure recovery.

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