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3 edition of Experimental study of shock wave interference heating on a cylindrical leading edge found in the catalog.

Experimental study of shock wave interference heating on a cylindrical leading edge

Experimental study of shock wave interference heating on a cylindrical leading edge

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Published by National Aeronautics and Space Administration, Langley Research Center, For sale by the National Technical Information Service in Hampton, Va, [Springfield, Va .
Written in English

    Subjects:
  • Heat -- Transmission.

  • Edition Notes

    StatementAllan R. Wieting.
    SeriesNASA technical memorandum -- 100484.
    ContributionsLangley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15293540M

    The optimum compression of an ideal gas by a cylindrical piston was considered by Zhdanov and Tribnikov [6] without forming any shock waves. In that case the sound wave fronts move with a sound velocity in front of the piston and this non-shock wave problem also needs numerical computations. Similar problem has. This effort investigates the dynamic properties of ejecta from explosively shocked, melted Pb targets. The study shows that the ejecta cloud that expands beyond the shocked surface is characterized by a high density and low velocity fragment layer between the free-surface and the high velocity micro-jetting particle cloud. This slow, dense ejecta layer is liquid by: EXPERIMENTAL ANALYSIS OF SHOCK WAVE EFFECTS IN COPPER Fabrice Llorca, Francois Buy, Jose Farre CEA Valduc, Is/Tille, France Abstract. This paper proposes the analysis of shock wave effects for a high purity copper. The method developed is based on the analysis of the mechanical behavior of as received and shocked materials. Wave breaking is a natural process involving transformation of wave energy into turbulent energy leading to a rapid transition of the free surface, that exerts massive hydrodynamic loads on marine structures [5]. A wave undergoes deformation, i.e. the wave height and local wave steepness increase as it propagates over decreasing water depth.


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Experimental study of shock wave interference heating on a cylindrical leading edge Download PDF EPUB FB2

Experimental study of shock wave interference heating on a cylindrical leading edge. Hampton, Va.: [Springfield, Va: National Aeronautics and Space Administration, Langley Research Center ; For sale by the National Technical Information Service.

MLA Citation. Wieting, Allan R. Get this from a library. Experimental study of shock wave interference heating on a cylindrical leading edge.

[Allan R Wieting; Langley Research Center.]. This paper presents the details of an experimental study of shock wave interference heating on a cylindrical leading edge representative of the cowl of a rectangular hypersonic engine inlet.

The study was conducted at Mach numbers ofand Get this from a library. Experimental Experimental study of shock wave interference heating on a cylindrical leading edge book of pressure and heating rate on a swept cylindrical leading edge resulting from swept shock wave interference.

[Christopher E Glass; United States. National Aeronautics and Space Administration.]. An experimental study of shock wave interference heating on a cylindrical leading edge representative of the cowl of a rectangular hypersonic engine inlet at Mach Experimental study of shock wave interference heating on a cylindrical leading edge book of, and is.

Wieting, A.R., “Experimental Study of Shock Wave Interference Heating on a Cylindrical Leading Edge,” NASA TMMay Google ScholarAuthor: Young J. Moon, Maurice Holt. A.R. Wieting, M.S. Holden — Experimental Study of Shock Wave Interference Heating on a Cylindrical Leading Edge at Mach 6 and 8.

AIAA paper 87–, (). Google ScholarCited by: 1. This paper presents the details of an experimental study of shock-wave interference heating on a cylindrical leading edge representative of the cowl of a rectangular hypersonic engine inlet.

The interaction of a cylindrical converging shock wave with an initially perturbed gaseous interface is studied experimentally. The cylindrical converging shock is generated in an ordinary shock tube but with a specially designed test section, in which the incident planar shock wave is directly converted into a cylindrical by: An experimental/numerical approach to shock-wave diffraction.

Compressibility effects on the propagation and interaction of shock-generated vortices. Shock-wave diffraction by an elastic sphere in water. Experimental study of shock wave interference heating on a cylindrical leading edge book Physics of a shock-generated freely moving compressible vortex.

Study of the propagation of shock waves over bodies by holographic interferometry. Nath, G. and Sahu, P. Propagation of a cylindrical shock wave in a mixture of a non-ideal gas and small solid particles under the action of monochromatic radiation.

Combustion, Explosion, and Shock Waves, Vol. 53, Issue. 3, p. CrossRef; Google ScholarCited by: number variation on the characteristics of the unsteady shock wave/turbulent boundary layer interaction generated by a blunt fin. A single blunt fin hemi-cylindrical leading edge diameter size was used in all of the experiments which covered the Math number range from to The measurements in thisFile Size: 7MB.

A numerical solution for the interaction of a moving shock wave with a turbulent mixing region, ([Albuquerque, N.M. Issued by Sandia Corp.], ), by William Fred Walker and Glen W. Zumwalt (page images at HathiTrust; US access only). Experimental study on the heat transfer in a separated flow by the interaction of shock wave/turbulent boundary layer is conducted.

The cylinder body is considered as a protruding body which makes the shock wave for the interaction with a boundary layer and its swept-back angle is selected as a by: 6.

The shock wave propagation over cylinders was also studied by Suzuki et al. [10]. In the Shock Wave Research Center of the Institute of Fluid Science, Tohoku University, in conjunction with train tunnel sonic boom problems, a preliminary study of effects of arrayed cylinders and spheres on shock attenuation propagating was conducted.

Aerodynamic heating in the blunt-fin induced shock wave/boundary layer interaction is investigated by means of numerical simulations.

The complex flow pattern on the flat plate is visualized by surface friction lines. The three-dimensional vortical structures and primary shock wave system in the interaction region are by: 1. turbulence on turbine blade leading edge film cooling. The study examines several test cases with two blowing ratios (BR= and ) and three mainstream turbulence intensities (, and %) using two types of leading edge models with cylindrical holes and diffuser holes [1].

The leading edge model consists of a semi-circular part of. Keyes J W, Hains F D. Analytical and experimental studies of shock interference heating in hypersonic flows. NASA TN D Khomik S V, Medvedev S P, Polenov A N, Gelfand B E.

Conditions of detonation initiation by focusing shock waves in a combustible gas mixture. Combustion, Explosion, and Shock Waves, AN EXPERIMENTAL STUDY ON THE SCATTERING OF EDGE-GUIDED WAVES BY A SMALL EDGE CRACK IN AN ISOTROPIC PLATE Benjamin S.

VIEN 1, L.R. Francis ROSE2, Wing Kong CHIU 1 1 Dpt Mechanical and Aerospace, Monash University, Clayton, VIC - Australia @, @ Experimental study on performance of vehicle penetrating into sand-like soil.

Takashi Abe, Experimental investigation of shock wave interference heating on a blunt body. Bertrand, A. Chpoun, Leading edge transition on a 76 degree swept cylinder at Mach Colin Coleman.

Introduction. Extracorporeal shock wave lithotripsy (ESWL) is a well-established treatment option for urolithiasis [1–3].However, the introduction of new lithotripters appears to have increased the potential problems of shock wave application compared with first-generation devices [4,5].Young urologists favour endourology and are less interested in ESWL, and at several centres, specially Cited by: Experimental Studies of Transitional Boundary Layer Shock Wave Interactions Xcyl = distance from plate leading edge to cylinder lead ing edge applications and from the formidable challenges that the study of such flows poses to b oth experiment and computation.

However, h igh Mach number air -breathing propulsion systems are of. Transmission of the interference filter 5 The "Curves of Growth" 6 Oscillcgram of emission signal behind shock wave at Iii = into 10 mm Hg of oxygen containing about sodium 7 Oscillcgram cfticublc-beam s~gnala for shock wave at i!I = into 10 mm Hg of oxygen containing about s sodium aFile Size: 1MB.

2 Computational study of shock waves propagating through air-plastic-water interfaces The shock-tube is a long cavity lled with air, where the shock wave pressure pro le can be measured. However, we don’t know what will happen when the shock wave interacts with Cited by: 2.

In addition to their own writings, Probstein and Hayes edited the English translation of a major text by two distinguished Russian physicists, Ya. Zel'dovich and Yu. Raizer, Physics of Shock Waves and High-Temperature Hydrodynamic Phenomena.

However, Dr. Probstein's literary Cited by: Coal mine gas disaster has the characteristic of destructive and complexity, in connection with the frequently of coal mine gas disaster, the paper studied on the propagation of gas explosion shock wave while pipe cross-sectional area changing from the experimental angle, designed the test system, the data of shock wave pressure when the pipe turning angle more or less than 90 degree was given Author: Yuan Fu, Ji Ren Wang, Bao Shan Jia.

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. Richtmeyer-Meshkov instability induced by cylindrical shock wave loading of cylindrical gaseous inhomogeneities. Application of the artificially blunted leading edge concept for directional control of high-speed vehicles.

Experimental study of. This proceedings present the results of the 29th International Symposium on Shock Waves (ISSW29) which was held in Madison, Wisconsin, U.S.A., from July 14 to J It was organized by the Wisconsin Shock Tube Laboratory, which is part of the College of Engineering of the University of.

The shock-wave system produced by the wing and recorded in the present test, is made up as follows: (a) A leading edge shock-wave. (b) Reflections of the leading-edge shock-wave from the surrounding tunnel walls. (c) A shock-wave associated with the trailing edge, and the sting support.

The parameters of a gas in a shock wave may be represented as a function of the Mach number M = v wave /a 0. In the limit, as M → ∞ and P 1 \p 0, → ∞ we obtain for strong shock waves. Thus, an arbitrarily strong shock wave cannot compress a gas by a factor greater than (γ + l)/(γ – 1).

They USE shock waves for chemical kinetics studies, for materials studies, and smashing kidney stones; they STUDY the phenomena associated with flows involving shock waves, such as supersonic flow, explosions, detonations, volcanic eruptions, and, in this symposium, even such with-it topics as impact of Shoemaker-Levy on Jupiter and blast waves.

An experimental study has been conducted using reflected type of shock tunnel to investigate the effect of shock wave impingement on supersonic combustion. In the experiment, air is compressed by reflected shock wave up to total temperature of K and total pressure of MPa. Shock heated air is used as a reservoir gas of supersonic nozzle.

A shock wave process (SWP) is a process of reorganizing a gas-dynamic wave interaction are called interference. Refraction of a moving shock wave at an inclined contact discontinuity is examined in this study. Shock wave refraction Several physical phenomena involving gas flows result in shock Size: KB.

EXPERIMENTAL STUDY OF SHOCK-DRIVEN, VARIABLE-DENSITY TURBULENCE USING A COMPLEX INTERFACE A Thesis Presented to The Academic Faculty by David Reilly In Partial Fulfillment of the Requirements for the Degree Master of Science in the Woodruff School of Mechanical Engineering Georgia Institute of Technology December The book begins with a brief history of shock wave research, the practical value of shock waves, and radiographs of shock and detonation waves to illustrate how they actually look.

Chapters 2 – 5 present experimental and the basic hydrodynamic and thermodynamic equations. Two industrial stainless steels were investigated under laser-shock loading in plasma confined regime with water at nearly 10 GW/cm2 irradiance, driving to stress loadings close to 7 GPa—20 ns at the surface of the targets.

A velocimetry interferometer system for any reflector was used to measure shock wave decay and estimate, through the determination of elastic precursors, the dynamic Cited by: on shock wave propagation.

Of particular interest is the analysis and optimisation of a gradual area reduction whereby a shock wave may be optimally strengthened. Experimental testing is conducted for a planar shock wave of A1s = propagating through one of three cornpound parabolic profiles ofor mm in length, all.

A wing leading -edge root fillet reduces the peak in wing root interference heating near the leading edge, and increasing Reynolds number increases the level of interference heating. The total heating to the windward surface of the swept wings was found to increase with increasing angle of attack (up to about 40°) and Reynolds number and to.

Experimental Investigation on Shock Wave and Turbulent The study of pseudo-shock waves has important implications for the design and operation of new air breathing engines for space planes, that is, the leading shock of the first shock, second shock and. Pdf. Introduction Pdf wave/boundary layer interaction (SWBLI) has been a topic of exhaustive research for the past several decades owing to its immutable complexity.1,2 SWBLI occurs when a shock wave impinges on a viscous boundary layer, which leads to either an increase in its shape factor or separation from the Size: 2MB.In the first campaign, an inclined interface download pdf is used as the initial condition.

The Mach number (), angle of inclination (60 degrees), and gas pair (N2/CO2) were held constant. The parameter which changed was the distance that the initial condition was placed relative to the end of the shock tube (i.e., the end of the test section).Author: David James Reilly.s the shock wave in water is attained depth km and shock wave in air reaches ebook height of 3 km ebook the symmetry axes.

Thereafter the shock wave in water is reflected from the bottom and interact with the primary wave. At t = s the shock wave in water is located at r = 6 km and already propagates over the underwater plateau. Later on.