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Monday, July 20, 2020 | History

2 edition of Wake-shock interaction at a Mach number of 6 found in the catalog.

Wake-shock interaction at a Mach number of 6

Walsh, Michael J.

Wake-shock interaction at a Mach number of 6

by Walsh, Michael J.

  • 83 Want to read
  • 33 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Office, for sale by the National Technical Information Service in [Washington], Springfield, Va .
Written in English

    Subjects:
  • Wakes (Aerodynamics),
  • Shock waves -- Mathematical waves.,
  • Compressibility.

  • Edition Notes

    StatementMichael J. Walsh ; Langley Research Center, Hampton, Va.
    SeriesNASA technical paper ; 1103, NASA technical paper -- 1103.
    ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Office., Langley Research Center.
    The Physical Object
    Pagination189 p. :
    Number of Pages189
    ID Numbers
    Open LibraryOL17537033M

    Cover design: eStudio Calamar Printed on acid-free paper 9 8 7 6 5 4 3 2 1 Preface This book, as a volume in the Shock Wave Science and Technology Reference Library, is primarily concerned with detonation waves or compression shock waves in reactive heterogeneous media, including mixtures of solid, liquid, and gas phases. unsteady aerodynamics, aeroacoustics and aeroelasticity of turbomachines Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines Edited by KENNETH C. HALL Duke University, Durham, North Carolina, U.S.A.

    Turbomachinery flows are among the most complex flows encountered in fluid dynamic practice (Lakshminarayana, ). The complexity is mainly reflected in the following areas (Chen, ): (1) Various forms of secondary flow caused by viscosity and complex geometry, which is dominated by vortex flows: passage, leakage, corner, trailing, horseshoe and scraping . "The many intense thermal environment was correct at mach 18 and also that's where we lost the particular vehicle." Columbia gone to call home in launch pad (12/09/02) The newsletter, dated April 4, furthermore stated your Columbia Accident Investigation Board has indicated "their belief which major actions will cover up throughout weeks.

    p.m., 10/03/03, Update: New launch target date; additional mission added As expected, NASA today set a new, more realistic target date for launch of the next shuttle mission - . Scribd es el sitio social de lectura y editoriales más grande del mundo.


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Wake-shock interaction at a Mach number of 6 by Walsh, Michael J. Download PDF EPUB FB2

Wake-shock interaction at a Mach number of 6. [Washington]: National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va.: For sale by the National Technical Information Service, (OCoLC) Material Type: Government publication, National government publication: Document Type: Book.

Two-dimensional flat plate wakes that have been described in Section can also be investigated, although only a few studies have been devoted to this wake interaction with a shock. Since the wake deficit that represents the driving velocity rapidly decreases downstream from the trailing edge, such shock interactions have to be analysed relative to the distance where the.

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). Wake, Shock, and Potential Field Interactions in a Stage Turbine—Part II: Vane-Vane Interaction and Discussion of Results Article (PDF Available) in Journal of.

Wake-shock interaction at a Mach number of 6 / ([Washington]: National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va.: For sale by the National Technical Information Service, ), by Michael J.

Walsh, Langley Research Center, and United States. Wake, Shock, and Potential Field Interactions in a Stage Turbine—Part I: Vane-Rotor and Rotor-Vane Interaction Article (PDF Available) in Journal of Turbomachinery (1).

Wake, Shock and Potential Field Interactions in a Stage Turbine—Part I: Vane-Rotor and Rotor-Vane Interaction,” ASME GT ASME J.

Turbomach. Cited by: Pressure and heat-transfer distributions in a simulated wing-elevon cove with variable leakage at a free-stream Mach number of W.

DEVEIKIS and W. BARTLETT. The paper shows that at typical design operating conditions shock interaction from the upstream blade row is an order of magnitude greater than wake interaction and that with the design vane-rotor inter-blade gap the presence of the rotor causes a periodic increase in the strength of the vane trailing edge by: 6.

Mixing-layer and wake shock interaction studies are less common, however. In the former case, the effects on the turbulence are not significant, and in the latter case the wake studies have focused on turbine blades in the transonic regime where other effects, such as unsteadiness and curvature, make it difficult to isolate the effect of the shock.

In physics, a shock wave (also spelled shockwave), or shock, is a type of propagating disturbance that moves faster than the local speed of sound in the medium. Like an ordinary wave, a shock wave carries energy and can propagate through a medium but is characterized by an abrupt, nearly discontinuous, change in pressure, temperature, and density of the medium.

The authors study a hydrodynamic model for semiconductors where the energy equation is replaced by a pressure-density relationship.

The authors construct artificial viscosity solutions, prove BV estimates independent of the viscosity coefficient and study the transonic weak limit.

The authors also. Volume 6, Issue 3. No Access. An interaction model of a supersonic laminar boundary layer on sharpand rounded backward facing steps.

ERIC BAUM Cited by: Free-surface wave-induced separation is studied for a surface-piercing NACA foil over a range of Froude numbers (0.2,) through computational fluid dynamics of the unsteady Reynolds-averaged Navier-Stokes and the continuity equations with the Baldwin-Lomax turbulence model, exact.

Full text of "DTIC ADA Aerodynamic Performance of Missile Configurations at Transonic Speeds Including the Effects of a Jet Plume" See other formats.

Simulation of the Interaction of Labyrinth Seal Leakage Flow and Main Flow in an Axial Turbine. Jan E. Anker, Ju¨rgen F.

Mayer. Pressure, Rotors, Turbines, Mach number, Flow (Dynamics), Reynolds number, Arches, Equilibrium (Physics), Fluctuations Wake, Shock and Potential Field Interactions in a Stage Turbine: Part I. Wake shock and potential field interactions in a stage turbine: Part 1- vane-vane interaction and discussion of results.

ASME Paper GT ASME Paper GT Google ScholarAuthor: Zhengping Zou, Songtao Wang, Huoxing Liu, Weihao Zhang. Full text of "NASA scientific and technical publications: A catalog of Special Publications, Reference Publications, Conference Publications, and. The cylindrical shock wave velocity (or Mach number) can be easily obtained from the expression for the pressure behind the shock front that is generally evaluated using the Hugoniot relationship.

It relates the vapour pressure behind the shock (p) and the ambient pressure (p 0), shock Mach number (M sw) and the ratio of specific heats. Full text of "Modern Exterior Ballistics The Launch And Flight Dynamics Of Symmetric Projectiles 2nd Ed.

Mc Coy" See other formats. A new EPA Publications Bibliography,(order number PB) again cumulates 7 years of EPA reports in a 2-part, hardbound publication which contains the same 7 indexes as the prior edition.

Quarterly supplements to this series continue to be published in the form of the EPA Publications Bibliography, Quarterly Abstract Bulletin.increased Mach number was incorporated in the new shock model discussed in Chapter 4. Thus, for supersonic blade sections, the parabolic term in Equation (A) was not used.

Second, the. increase in imin with Mach number was observed to be too large (as high as 15 degrees), even for. subsonic airfoil sections.Inflation and drag characteristics of a foot ( meter) nominal-diameter cross parachute, deployed at a Mach number of and a dynamic pressure of lb/sq f t ( N/m(exp2)), were obtained from the fourth balloon-launched flight test of the Planetary Entry Parachute Program (PEPP).