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Sunday, July 12, 2020 | History

2 edition of Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds found in the catalog.

Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds

William A. Cassels

Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds

by William A. Cassels

  • 104 Want to read
  • 13 Currently reading

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

    Subjects:
  • Boundary layer.,
  • Body of revolution.,
  • Aerodynamics, Supersonic.

  • Edition Notes

    Statementby William A. Cassels and James F. Campbell.
    SeriesNASA technical note, NASA TN D-6063
    ContributionsCampbell, James F. 1941- joint author.
    Classifications
    LC ClassificationsTL521 .A3525 no. 6063
    The Physical Object
    Pagination67 p.
    Number of Pages67
    ID Numbers
    Open LibraryOL4855008M
    LC Control Number75610175

    Others, including shock-boundary-layer interaction, are discussed from a qualitative point of view. The book includes 60 examples and more than practice problems. The authors also offer analytical methods such as Method of Characteristics (MOC) that allow readers to practice with the subject matter. This book is an attempt to tackle the boundary layer theory in an organic, fairly complete, modern fashion. Addressed to readers with a lower level of sophistication than the Schlichting book, and not as thorough, this book covers all the basics, has a better pedagogy and interesting computer applications, albeit written in Java (!).Cited by:

    At the bottom of the boundary layer, however, the temperature stays almost as high as at the stagnation point due to frictional heating. In a turbulent boundary layer on a flat plate the frictional effect would increase temperature by °C. Without the pressure distribution over the wing I cannot give a value for the absolute temperature, though. Swept-back and triangular delta wings and boundary-layer control reduce drag. A shock wave causes a thunderlike sonic boom as it spreads away from the plane. Sometimes persons on the ground can hear the boom. The shock wave may even break windows. Supersonic speeds are faster than the speed of .

    aerodynamics is the study of. The boundary layer of a body in a moving airstream is: A thin layer of air over the surface in which the air is retarded by the effects of friction. Skin Friction drag resulting from a laminar boundary layer will be: transition point. laminar flow has.   On this basis, we might as well make the somewhat daring speculation that the low-speed streak is composed of waves and that the pocket is a local three-dimensional wave. The fact that the low-speed streak is composed of waves has been testified by a .


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Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds by William A. Cassels Download PDF EPUB FB2

TURBULENT-BOUNDARY- LAYER CHARACTERISTICS OF POINTED SLENDER BODIES OF REVOLUTION AT SUPERSONIC SPEEDS By Jerry M. Allen and William J. Monta Langley Research Center SUMMARY An experimental investigation has been performed at free- stream Mach numbers of and over a free-stream Reynolds number range from X to 27 X lo6Cited by: 5.

Filed under: Body of revolution. Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds, (Washington, National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], ), by William A.

Cassels and James F. Campbell (page. Boundary-layer transition study of several pointed bodies of revolution at supersonic speeds, (Washington, National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], ), by William A.

Cassels and James F. Campbell (page images at HathiTrust; US access only). Abstract. Boundary-layer transition is a problem that has plagued several generations of aerodynamicists. There are very few things about transition that are known with certainty, other than the fact that it happens if the Reynolds number is large by: The transition of the boundary layer from the laminar to the turbulent state on a smooth flat plate at a zero angle of attack is studied in the range of Mach numbers M∞= 2–6.

It is demonstrated that Cited by: 3. 3 Methods of Fixing Boundary Layer Transition General A guide to the size of transition wires Method of correlation The critical value of RI., Table I The effects of fixing boundary layer transition on flow separation on a double wedge aerofoil at low Reynolds Numbers.

Transition of the boundary layer on a flat plate at supersonic and hypersonic velocities Article (PDF Available) in Thermophysics and Aeromechanics 16(3) Author: Vladimir Kornilov. Studies of the Turbulent Boundary Layer on Waisted Body of Revolution in Subsonic and Supersonic Flow By K.

WINTER*, J. ROTTA** and K. SMITH*** a Reports and Memoranda No. t August, Summary. The object of the study was to determine the influence of Mach number, pressure gradients and stream. THREE DIMENSIONAL BOUNDARY LAYER TRANSITION ANALYSIS IN SUPERSONIC FLOW USING A NAVIER-STOKES CODE (NS) analysis are summarized in section 2.

The results of transition analysis on the sharp cone, the nose cone, and the natural laminar flow wing of the experimental airplane are described in section 3, 4 and 5 respectively. The linear boundary-layer theory described in Section can be generalized to allow for the nonlinear effect discussed earlier.

The assumptions listed in Section are valid for the nonlinear boundary-layer theory as well. In particular, the decompositions in Eqs. () remain valid. Since the nonlinear effect shows itself only under shell local bending, the terms with index “p.

The boundary-layer transition characteristics of two bodies of revolution, a flat plate, and an unswept wing in a low-turbulence wind tunnel by Boltz, F.

; Kenyon, G. ; Allen, C. Full text of "The boundary-layer transition characteristics of two bodies of revolution, a flat plate, and an unswept wing in a low-turbulence wind tunnel" See other formats NASAJTN _D LOAN- COPY: EKT-yHN TO ^ i o in m I- 5 • LAYER TRANSITION CHARACTERISTICS OF TWO BODIES OF REVOLUTION, A FLAT PLATE, AND AN UNSWEPT.

In addition to a smooth plate without trips, three different trip configurations (loca- tions 2nd widths) were tested. The size of the roughness particles was varied from a size below that required to fix transition to a size larger than the boundary-layer thick- ness at the trip.

The investigation was conducted in the Langley inch variable supersonic tunnel. Transition and Stability of High-Speed Boundary Layers Article in Annual Review of Fluid Mechanics 43(1) January with 88 Reads How we measure 'reads'. the oblique waves in the boundary layer are above the level of the plane wave at β≈0.

Keywords— receptivity, supersonic boundary layer, blunted leading edge, stability, transformation coefficient. INTRODUCTION REDICTION of laminar-turbulent transition of supersonic boundary layer remains an unsolved problem despite a.

The transitional state of a boundary layer is that state during which the boundary layer passes from fully laminar to fully turbulent. This passage can be either induced or natural, and it was represented in this thesis work by the trigger wake and by the boundary layer flow downstream of the release point of an electric spark, : Henny Bottini.

Allen and A. Eggers, Jr., "A Study of the Motion and Aerodynamic Heating of Ballistic Missiles Entering the Earth's Atmosphere at High Supersonic Speeds," NACA Conf.

Research Memo. A53D28, Aug. The NACA published updated versions of this same report as TN and TR (). Adventures in Research, p. The test case considered for validation of the new transition model in high speed flow is from Mee. 30 Experiments were carried out in the T4 free-piston shock tunnel at University of Queensland for a m long and m wide flat plate.

Frauholz et al. 31 studied the case extensively based on the γ-Re θ t transition model with modified correlations, and satisfactory results were by: 7.

You can write a book review and share your experiences. Other readers will always be interested in your opinion of the books you've read. Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them.

Boundary-layer transition and displacement-thickness effects on zero-lift drag of a series of power-law bodies at Mach 6 (NASA technical note) [George C Ashby] on.

Transition prediction for oblique breakdown in supersonic boundary layers with uncertain disturbance spectrum G. Serino, O. Marxeny, F. Pinna z, P. Rambaud x and T.E. Magin{Aeronautics and Aerospace Department, von Karman Institute for Fluid Dynamics, Belgium Laminar to turbulent transition in supersonic boundary layer is numerically investigatedCited by: 4.have many advantages for use in a retrieval system.

Experience in its practical application was desired. Tests had already been carried out with a Uniterm system for cataloguing aircraft structural data (), and on the N.L.L. card catalogue of aerodynamic measurements (3, 4).Similar evaluation of a peek-a-boo device based on a suitable subject classification was considered desirable.American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA