scholarly journals An Analytical Method for the Response of Coated Plates Subjected to One-Dimensional Underwater Weak Shock Wave

2014 ◽  
Vol 2014 ◽  
pp. 1-13 ◽  
Author(s):  
Zeyu Jin ◽  
Caiyu Yin ◽  
Yong Chen ◽  
Xiuchang Huang ◽  
Hongxing Hua
Keyword(s):  
Shock Wave ◽  
Analytical Method ◽  
Weak Shock ◽  
Wave Theory ◽  
Time Sequence ◽  
Weak Shock Wave ◽  
One Dimensional ◽  
Coated Plate ◽  
Pressure Increment ◽  
Good Agreement

An analytical method based on the wave theory is proposed to calculate the pressure at the interfaces of coated plate subjected to underwater weak shock wave. The method is carried out to give analytical results by summing up the pressure increment, which can be calculated analytically, in time sequence. The results are in very good agreement with the finite element (FE) predictions for the coating case and Taylor’s results for the noncoating case, which validate the method that is suitable for underwater weak shock problem. On the other hand, Taylor’s results for the coating case are invalid, which indicates a potential application field for the method. The extension of the analytical method to q-layer systems and dissipation case is also outlined.

Weak shock reflection from an open end of a tube with a baffle plate

2003 ◽  
Vol 217 (6) ◽  
pp. 651-659 ◽  
Author(s):  
H D Kim ◽  
Y H Kweon ◽  
T Setoguchi ◽  
T Aoki
Keyword(s):  
Shock Wave ◽  
Boundary Condition ◽  
Empirical Equation ◽  
Weak Shock ◽  
Weak Shock Wave ◽  
Baffle Plate ◽  
Numerical Investigations ◽  
Weak Shock Reflection ◽  
Inviscid Compressible Flow ◽  
Good Agreement

The present paper describes experimental and numerical investigations of a new boundary condition at an open end of a tube, in which a weak shock wave is discharged towards the surroundings. Experimental and computational investigations were performed on a simple shock tube with and without baffle plates. A numerical calculation was carried out for an unsteady, axisymmetric, inviscid, compressible flow. The size of baffle plate was varied in order to understand its effect on the reflection of the weak shock wave from the open end of the tube. With and without a baffle plate, the results of the experiment were in good agreement with those of numerical calculations. The results showed that an open end correction is subject to the presence of a baffle plate at the open end. An improved empirical equation for the reflection of the weak shock wave from the open end of a duct with and without a baffle plate was developed.

Evolution of weak shock wave in two-dimensional steady supersonic flow in dusty gas

2019 ◽  
Vol 160 ◽  
pp. 552-557 ◽  
Author(s):  
Rahul Kumar Chaturvedi ◽  
Pooja Gupta ◽  
L.P. Singh
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Weak Shock ◽  
Weak Shock Wave ◽  
Dusty Gas ◽  
Two Dimensional

The determination of arc temperatures from shock velocities

1957 ◽  
Vol 240 (1220) ◽  
pp. 54-66 ◽  
Keyword(s):  
Shock Wave ◽  
Strong Shock ◽  
Weak Shock ◽  
Wave Theory ◽  
New Method ◽  
Shock Propagation ◽  
Plane Shock ◽  
Gas Temperature ◽  
Specific Heats ◽  
Arc Discharges

The measurement of the high gas temperatures associated with arc discharges requires special techniques. One such method, developed by Suits (1935), depends on the measure­ment of the velocity of a sound wave passing through an arc column, although in fact Suits measured the velocity of a very weak shock wave. The new method described in the present paper is one in which temperatures are determined from the measurement of the velocity of a relatively strong shock wave propagated through an arc. The new method has the merit of consistently producing accurately measurable records and of increasing the accuracy of the temperature determination. The shock velocities are measured by means of a rotating mirror camera. Within the arc, the shock propagation is observable by virtue of the increased arc brightness produced by the shock. In the non-luminous regions surrounding the arc, the shock propagation is displayed by means of a Schlieren system. The interpretation of the measurements depends upon a one-dimensional analysis given in this paper which is similar to that of Chisnell (1955) and which describes the interaction of a plane shock with a con­tinuously varying temperature distribution. In our analysis account is taken also of the continuous variation in specific heats and molecular weight which are of importance under high gas temperature conditions. In practice plane wave theory cannot adequately describe the shock propagation, since attenuation occurs both in the free gas and in the arc column. The effects of this attenuation on the temperature determinations may be accounted for by the use of an experimentally determined attenuation relationship given in the paper. The finally developed method yields temperature values to an accuracy of ± 2%. Experiments are described for carbon and tungsten arcs in air and nitrogen for currents up to 55 amperes and pressures up to 3 atmospheres. The values obtained range from 6200 to 7700° K and are in good agreement with values determined by other techniques.

The physical nature of weak shock wave reflection

2005 ◽  
Vol 542 (-1) ◽  
pp. 105 ◽  
Author(s):  
BERIC W. SKEWS ◽  
JASON T. ASHWORTH
Keyword(s):  
Shock Wave ◽  
Wave Reflection ◽  
Weak Shock ◽  
Physical Nature ◽  
Weak Shock Wave ◽  
Shock Wave Reflection

A numerical study of weak shock wave propagation in a reactive bubbly liquid

Shock Waves ◽  
1996 ◽  
Vol 6 (5) ◽  
pp. 287-300 ◽  
Author(s):  
P. Mazel ◽  
R. Saurel ◽  
J. -C. Loraud ◽  
P. B. Butler
Keyword(s):  
Shock Wave ◽  
Wave Propagation ◽  
Numerical Study ◽  
Weak Shock ◽  
Shock Wave Propagation ◽  
Weak Shock Wave ◽  
Bubbly Liquid

On the interaction between shock waves and boundary layers

1951 ◽  
Vol 47 (3) ◽  
pp. 545-553 ◽  
Author(s):  
K. Stewartson
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Reynolds Number ◽  
Shock Waves ◽  
Boundary Layers ◽  
Weak Shock ◽  
Boundary Layer Separation ◽  
Weak Shock Wave ◽  
Layer Separation ◽  
Boundary Layer Equations

AbstractThe effect on the boundary-layer equations of a weak shock wave of strength ∈ has been investigated, and it is shown that ifRis the Reynolds number of the boundary layer, separation occurs when ∈ =o(R−i). The boundary-layer assumptions are then investigated and shown to be consistent. It is inferred that separation will occur if a shock wave meets a boundary and the above condition is satisfied.

scholarly journals Shock Initiation of a Satellite Tank under Debris Hypervelocity Impact

2019 ◽  
Vol 9 (19) ◽  
pp. 3957
Author(s):  
Zhao ◽  
Zhao ◽  
Cui ◽  
Wang
Keyword(s):  
Shock Wave ◽  
Power Density ◽  
Wave Theory ◽  
Hypervelocity Impact ◽  
Shock Initiation ◽  
One Dimensional ◽  
Minimum Power ◽  
Shock Wave Pressure ◽  
The One ◽  
Debris Impact

For the risk assessment of a satellite to determine whether the satellite tank explodes under the hypervelocity impact, the Walker–Wasley criterion is selected to predict the shock initiation of the satellite tank. Then, the minimum power density of liquid hydrazine is determined based on the tests, the expressions of shock wave pressure and pressure duration are constructed based on the one-dimensional wave theory, and the initiation criterion for the liquid hydrazine tank is established. Finally, numerical simulation and the initiation criterion are adopted to calculate the power density in the satellite tank under the debris impact at the velocity of 10 km/s. The calculated power density agrees well with the simulated power density, they are both larger than the minimum power density, demonstrating that the shock wave generated by the hypervelocity impact is sufficient to trigger an explosion in the satellite tank.

scholarly journals The experimental study of the weak shock wave action on the boundary layer of the sweep flat plate

2019 ◽  
Vol 1404 ◽  
pp. 012083
Author(s):  
V L Kocharin ◽  
A D Kosinov ◽  
A A Yatskikh ◽  
L V Afanasev ◽  
Yu G Ermolaev ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Experimental Study ◽  
Flat Plate ◽  
Weak Shock ◽  
Wave Action ◽  
Weak Shock Wave
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