2 edition of ** analytical and numerical study of a shock wave interaction with an area change.** found in the catalog.

analytical and numerical study of a shock wave interaction with an area change.

David Robert Greatrix

- 32 Want to read
- 2 Currently reading

Published
**1982** .

Written in English

The Physical Object | |
---|---|

Pagination | [90] leaves |

Number of Pages | 90 |

ID Numbers | |

Open Library | OL14744795M |

EXPERIMENTAL STUDY OF SHOCK WAVE INTERACTING PLANE GAS-PLASMA BOUNDARY 3 exposition of the discharge flash. ‘Fig. 4’ and ‘Fig. 5’ are the images of discharge’s area with plate shock wave M= Experiments showed that discharge concentrated in the low pressure area in front of shock wave. Also we can see that lighting is not homogeneous. Joel Smoller and Blake Temple have established classes of shock wave solutions to the Einstein Euler equations of general relativity; indeed, the mathematical and physical con sequences of these examples constitute a whole new area of : Hardcover. The wave generation in the numerical wave tank is based on a relaxation method proposed by Larsen and Dancy [31] and Jacobsen et al. [32]. The wave absorption is employed using the active absorbing beach [33]. The total wave force on a vertical cylinder from breaking waves is computed based on the pressure p and the. 3. Numerical Validation. In order to validate the capability of the model to model wave-current interaction, the model results were compared to those reported by Chen et al. [] for a uniform current with regular waves over a constant water depth under various wave and current , an analytical solution [] is used to validate the case of a shear current with regular by: 1.

Touré, Patrice und Schülein, Erich () Study of 2-D Shock-Wave / turbulent Boundary Layer Interaction. AIAA Aviation , Juni , Denver, Colorado, USA. Dieses Archiv kann nicht den gesamten Text zur Verfügung by: 2.

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An analytical study of separated flows induced by shock wave - boundary layer interaction by m, s, holden prepa red by cornell aeronautical laboratory, inc.

buffalo, n. for goddard space flight center national aeronautics and space administration l washington, d.

l october File Size: 3MB. The problem of shock interaction with a rigid circular cylinder has been investigated using a compressible immersed boundary method coupled with high-order weighted-essentially non-oscillatory (WENO) scheme.

First, the accuracy of the developed code is validated. Then, influences of the incident shock Mach number on the flow-field structure and dynamic drag coefficient, as well as time Cited by: 2. Numerical and theoretical analysis of shock waves interaction and reflection K. Alhussan Space Research Institute, King Abdulaziz City for Science and Technology, Saudi Arabia Abstract This paper will show numerical and theoretical analysis of shock waves interaction and reflection.

In this paper some characteristics of non-steady. Abstract. The interaction of a planar shock wave with a high-density layer has been investigated both numerically and analytically. It has been shown that depending on the incident shock wave Mach number and the densities ratio across the interface the interaction results in either a stationary regular reflection or a stationary Mach : D.

Rayevsky, G. Ben-Dor. The wave patterns that occur when a shock wave interacts with an abrupt area change are analyzed in terms of the incident shock wave Mach number and area jump ratio. The solutions predicted by a self-similar model are in good agreement with those obtained numerically from the quasi-one-dimensional time-dependent Euler by: 9.

This work concerns the reflected shock wave/boundary layer interaction in a shock tube. The numerical simulation of this problem necessitates numerical schemes which are robust and very accurate.

The paper presents a numerical study of the interaction of a shock wave with a protective stopping. It addresses the effect of the type of setting on dangerous stresses emergences under the explosion.

The types of setting are evaluated depending on the nature of the load on the sopping. Heavy concrete of B15 grade was taken as the material for : A.E. Baganina, D.Y. Paleev, Beglyakov.

In this work the problem of wave-body interaction is studied from the point of view of analytical dynamics. The liquid is considered inviscid, incompressible, unbounded, with an unbounded free. structural loads generated by a shock wave/boundary layer interaction (SWBLI or SBLI).

In conjunction with an experimental campaign produced within the research group, a numerical study was performed using a semi-infinite cylinder to generate a SWBLI at Mach with both laminar and turbulent boundary layers.

The goals were not only toCited by: 1. A sample of results, showing overpressure recorded by Ohtomo et al. for the barrier shown in Fig.

1, and their present simulations is presented in Fig. 5, Fig. 6 for two cases. In Fig. 5, the incident shock wave Mach number was and in Fig. 6 the incident shock wave Mach number was Being aware of the multiple shock reflections between neighboring plates of the barrier and shock Cited by: 6.

Then shock C2 intersects the oblique shock C1 at point H, from which emanate the two refracted shocks C3 and C4. The point H could be seen clearly in the Schlieren pictures[2] oat deflection angles of o, 8o, and For the accuracy of numerical results, the treatment of the sublayer, which is very close to the solid wall, plays an.

Flow Instability in Shock Tube Due to Shock Wave-Boundary Layer-Contact Surface Interactions, a Numerical Study Introduction It is becoming increasingly difficult to ignore the role of short duration high speed flow test facilities.

When an object moves faster than the speed of sound, and there is an abrupt decrease in the flow area, shock waves are generated.

Shock waves are very thin regions in the gas where the gas properties change by a large amount. In many flow problems multiple shocks are present. To study the primary effects on biological tissue, an experimental blast wave that simulates a real blast wave is required.

Shock tubes can be used for this purpose, and such a tube is now under use in our laboratory. The objective of this thesis is to describe numerical simulations used to characterize the performance of this shock tube. Experimental and numerical study of shock wave propagation over cylinders and spheres A.

Abe', K. ~akayama', K. Itoh2 I Shock Wave Research Center of Institute of Fluid Science. Tohoku University, Japan 2 Kakuda Research Center, National Aerospace Laboratory, Japan Abstract.

Underwater explosion is very important for underwater weapons-design technology and research on the damage effect of target structure.

In this paper, the flow-out boundary and variable step-size multi-material Euler algorithm were utilized to analyze numerically the whole process of shock wave generation and propagation, as well as bubble formation and impulse of underwater : Wei Ju, Yi Liu, Jue Ding.

Analysis of unsteady eﬀects in shock/boundary layer interactions By S. Pirozzoli†, J. Larsson, J. Nichols, M. Bernardini†, B. Morgan AND S. Lele The dynamics of interactions between impinging shock waves and turbulent boundary layers in supersonic ﬂow is analyzed by mining a LES database developed for several.

Direct numerical simulations (DNS) are conducted for a Mach turbulent boundary layer interacting with an impinging shock at three different shock incidence angles.

The accuracies of DNS calculations are established by checking the convergence of flow statistics for various grids, by comparing the generated results with those in the literature and also by the balance of contributing terms Cited by: the interaction of plane shock waves with curved gas interfaces.

In a related problem, Markstein (a, b) and Rudinger () studied the interaction of shock waves with curved flame fronts, and so considered the curved slow-fast case. Precursors and lateral shocks associated with the phenomenon of irregular refraction were Size: 5MB. The large eddy simulation (LES) of a compression ramp shock wave and turbulent boundary layer interaction (STBLI) is presented.

The ramp angle is 24 and the incoming boundary layer ow conditions are Mach and Re The LES data are in good agreement with existing direct numerical simulation (DNS) data with the same incoming ow parameters.

Analytical linear theory for the interaction of a planar shock wave with a two- or three-dimensional random isotropic density field. Huete Ruiz de Lira C(1), Velikovich AL, Wouchuk JG. Author information: (1)Escuela Técnica Superior de Ingenieros Industriales, Universidad de Castilla La Mancha, Campus s/n, Ciudad Real, Spain.

Cited by: The accurate numerical simulation of shock wave / turbulent boundary layer interactions (SBLIs) remains one of the more challenging problems in computational fluid dynamics. Such interactions induce high fluctuating pressure and heat transfer loads and can cause flow separation that can lead to.

the shock wave lies 1.n a phne parallel to the surface on which the boundary layer interaction is being studied. This case is referred to here as a "glancing" interaction b&:een a shock M~VC end a boundary layer.

The present investigation wa s undertaken to provide information on the. Numerical and experimental studies of structures loaded by a shock wave (pressure impulse) are burdened with many ex-perimental, numerical and analytical errors.

A phenomenon of impact of a pressure impulse into a ﬂat barrier has been described quite extensively. In the case of an impact of a shock wave into a plate positioned at a certain.

The Interaction between a Weak Normal Shock Wave and a Turbulent Boundary Layer -By- G. Gadd, Ph.D. of the Aerodynamics Division, N.P.L.

19th June, SUMMARY A theory is presented for the interaction between a weak normal shock in an initially uniform mainstream, and an idealisedFile Size: 2MB. The improved GFM is applied to the collapse of a single spherical bubble. The present results are in good agreement with those obtained from the equation of motion for a single bubble (Keller equation) coupling with the energy equation.

The improved multigrid GFM is also applied to the interaction of a gas bubble with a strong shock by: 1. Shock Waves in Gas Dynamics 61 Courant-Friedrichs™s book [19] gives the account of the e⁄orts on the equations by many of the leading mathematicians before A basic feature of hyperbolic systems of conservation laws is that there are rich phenomena of wave interactions involving shock waves and contact discontinuities.

- Shock Wave Boundary-Layer Interactions Edited by Holger Babinsky and John K. Harvey Frontmatter More informatio n SHOCK WAVE–BOUNDARY-LAYER INTERACTIONS Shock wave–boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft.

The analytical solutions provide the practicing engineer with computational speed in obtaining results for overland flow problems, and a means to check the validity of the numerical models. On the other hand, for larger scale catchment-stream problems, the verified numerical methods provide efficient and accurate algorithms to obtain solutions.

velocity) change discontinuously is called a shock many cases; however, a detailed picture of the shock is not required; since the shock thickness (λd is much smaller than the lengthscales of gradients in the gas on each side of it, we can approximate the shock as a discontinuity in the gas ﬂow.

The connection be-File Size: KB. Abstract. An experimental and numerical study of shock wave loading on a cylin-drical water column is presented. Experiments were conducted in a 4 mm x mm shock tube equipped with holographic interferometry.

The cylindrical water column had a diameter of mm and height of 4 mm. It was exposed to a shock wave of Mach number in. It is proposed the exact solution of the problem of a convergent shock wave and gas dynamic compression in a spherical vessel with an impermeable wall in Lagrangian coordinates.

At the initial time the speed of cold ideal gas is equal to zero, and a negative velocity is set on boundary of the sphere. When t > t0 the shock wave spreads from this point into the by: 2.

Shock wave laminar boundary layer interaction (SWBLI) [Houghton et al., ] References [1] Degrez G., Boccadoro C. H., and Wendt J.

() The interaction of an oblique shock wave with a laminar boundary layer revisited. An experimental and numerical study, J. Numerical Investigation of Shock wave Turbulent Boundary Layer Interaction 27 on surface pressure and shear stress distributions.

A qualitative description of the interaction is also presented based on density contours. Fig. 1: Shock wave on aircraft [5] Fig. 2: Inviscid supersonic flow over compression corner generating an oblique. A transonic interaction between a shock wave and a turbulent boundary layer is experimentally and theoretically investigated.

The configuration is a transonic channel flow over a bump, where a shock wave causes the separation of the boundary layer and a recirculating bubble is. We construct the solutions to the strong shock wave problem with generalized geometries in nonideal magnetogasdynamics. Here, it is assumed that the density ahead of the shock front varies according to a power of distance from the source of the disturbance.

Also, an analytical expression for the total energy carried by the wave motion in nonideal medium under the influence of magnetic field is Cited by: 2. sonic point on the bow shock wave. b) Type II interaction reflects the Mach phenomenon [14, ] and produces two triple points separated by a normal shock after the intersection of the two oblique shock waves.

c) If the oblique shock crosses the strong bow shock, a. This thesis presents a study of wave interaction with porous seabeds and porous breakwaters by employing a two-dimensional numerical model extended from an earlier developed model named COBRAS (Liu et al., ).

In the present numerical model the flow outside the porous media is described by the Reynolds Averaged. Numerical investigation of interaction between shock waves and dusty ﬂows S. Carcano a; a MOX - Modelling and Scientiﬁc Computing, Dipartimento di Matematica “F. Brioschi”, Politecnico di Milano Via Bonardi 9, Milano, Italy [email protected] Abstract.

Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and : Cambridge University Press. An Analytical and Experimental Study of Energy Loss for Progressive Linear Waves Interacting with Thin Porous Medium in an Infinitely Long Channel By David Buchanan With the help and supervision of Dr.

K. H. Wang-Faculty Mentor and Mr. Ted Chu-Graduate Mentor.Shock-wave boundary-layer interaction study on a compression corner using pressure-sensitive paint. Shock-wave boundary-layer interaction study on a compression corner using pressure-sensitive paint”,International Journal of Aerospace Innovations, Volume 4, Issue ,1 MarchPages numerical simulation using Sandia's CTH hydrocode.

In simulations and experiments, the air behind the water sheet experiences two distinct pressure peaks. An initial pressure rise results from the passage of a low pressure shock wave (M ≈ 1) through the intact sheet and into the air downstream of the water sheet.

Following this, the.