Last edited by Tujinn
Sunday, July 19, 2020 | History

2 edition of Pressure on axisymmetric base in a transonic or supersonic free stream in the presence of a jet found in the catalog.

Pressure on axisymmetric base in a transonic or supersonic free stream in the presence of a jet

Michael H. Harries

Pressure on axisymmetric base in a transonic or supersonic free stream in the presence of a jet

by Michael H. Harries

  • 316 Want to read
  • 5 Currently reading

Published by Flygtekniska försöksanstalten; Almqvist & Wiksell (distr.) in Stockholm .
Written in English

    Subjects:
  • Aerodynamics.,
  • Nozzles.,
  • Air jets.

  • Edition Notes

    Statementby M. H. Harries.
    SeriesFlygtekniska försöksanstalten. Meddelande, 111
    Classifications
    LC ClassificationsTL507 .U45 no. 111
    The Physical Object
    Pagination31 p.
    Number of Pages31
    ID Numbers
    Open LibraryOL4931985M
    LC Control Number76358778

    CiteSeerX - Document Details (Isaac Councill, Lee Giles, Pradeep Teregowda): The main purpose of this study is to investigate transonic flow over an axisymmetric rigid body of revolution using matched asymptotic theory of high Reynolds number flow. To achieve this goal, triple-deck structure was constructed over the rigid body. It is found that in the axisymmetric transonic flow the. the free charge density, is the fluid density, is the dynamic viscosity, K is electric conductivity and t is the time variable. The geometry we use is shown in Figure 1. Figure 1. Electrospinning model The internal pressure in the jet can be found by taking into consideration the balances across the.

    Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection An investigation of the transonic pressure drag coefficient for axi-symmetric bodies. A Computer Program for the Aerodynamic Design of Axisymmetric and Planar Nozzles for Supersonic and Hypersonic Wind Tunnels [J. C. Sivells] on *FREE* shipping on qualifying offers. A Computer Program for the Aerodynamic Design of Axisymmetric and Planar Nozzles for Supersonic and Hypersonic Wind TunnelsAuthor: J. C. Sivells.

      We use input-output analysis to predict and understand the aeroacoustics of high-speed isothermal turbulent jets. We consider axisymmetric linear perturbations about Reynolds-averaged Navier-Stokes solutions of ideally expanded turbulent jets with jet Mach numbers Cited by: by varying the ambient pressure. For studying the effect of jet exit Mach number on the structure of underexpanded jet ejected into still air, a constant NPR of is considered. Three different jet exit Mach numbers 2, , and are used here. Finally, the cases with the jet exhausted into a supersonic stream.


Share this book
You might also like
Teachers As Leaders

Teachers As Leaders

Lay leaders

Lay leaders

Memorial of the New Orleans and Pacific Railroad Company.

Memorial of the New Orleans and Pacific Railroad Company.

Methods for allocating highway costs

Methods for allocating highway costs

Felt with love

Felt with love

Y. Tookay is coming!

Y. Tookay is coming!

Passages 3e and paperback dictionary

Passages 3e and paperback dictionary

Sorrow and song

Sorrow and song

Relationships between isoenzymes , cultural characters, and pathogenicity in Ceratocystis ulmi (buism.) C. Moreau.

Relationships between isoenzymes , cultural characters, and pathogenicity in Ceratocystis ulmi (buism.) C. Moreau.

handy book of fishery management.

handy book of fishery management.

Office furniture

Office furniture

Memorial of Joseph and Lucy Clark Allen (Northborough, Mass.)

Memorial of Joseph and Lucy Clark Allen (Northborough, Mass.)

Porsche

Porsche

Pressure on axisymmetric base in a transonic or supersonic free stream in the presence of a jet by Michael H. Harries Download PDF EPUB FB2

And improvement in design will suits the commercial jet planes. Key Words: boat tail nozzle, computational software (GAMBITFLUENT ) 1. INTRODUCTION Computational fluid dynamics analyses of an axisymmetric nozzle at transonic free stream conditions have been completed to determine the capabilities of Reynolds.

Abstract. The outflow of an axisymmetric jet into a cylindrical channel of arbitrarily large cross-sectional area is considered. A method is proposed for analysis of the base pressure in the separation zone bounded by the inviscid jet boundary, the channel wall, and the : Ya.

Vagramenko, A. Puchkova. CALCULATION OF THE PRESSURE DISTRIBUTION ON AXISYMMETRIC BOATTAILS INCLUDING EFFECTS OF VISCOUS INTERACTIONS AND transonic, and supersonic speeds are P./P ratio of jet total pressure to free stream static pressure R radius of. Effect of Axisymmetric Sonic Nozzle Geometry on Characteristics of Supersonic Air Jet Article in Journal of Thermal Science 13(2) May with 54 Reads How we measure 'reads'.

Mach number contours for supersonic axisymmetric nozzle jet flow. Flow Description. This case involves a "submerged" turbulent supersonic jet emanating from an axisymmetric convergent-divergent Mach nozzle.

This nozzle was studied by J.M. Eggers in Velocity profiles and eddy viscosity distributions were obtained within the jet. The model was mounted in supersonic free streams of Mach 2 and 3 produced by the Delft University transonic/supersonic wind tunnel.

The jet exhausting from the nozzle had an exit Mach number of 4. An extensive experiment-al investigation have the jet Mach number. These numerical studies of been carried out on the axisymmetric jets exhaust- free jets reveal that the time-marching method can irig from sonic and supersonic nozzles into still capture the flow field features of free jets,File Size: KB.

A comprehensive study of a steady axisymmetric supersonic jet of CO 2, including experiment, theory, and numerical calculation, is experimental part, based on high-sensitivity Raman spectroscopy mapping, provides absolute density and rotational temperature maps covering the significant regions of the jet: the zone of silence, barrel shock, Mach disk, and subsonic Cited by: Despite the simplicity of the body shape, supersonic flow over a straight cone with circular cross section is known to exhibit a rich transition behavior.

At a zero angle of incidence (α = 0), the boundary layer flow is axisymmetric; hence, transition at supersonic free-stream Mach numbers is dominated by first mode instability. At nonzero anglesCited by: 4. Secondary growth of base pressure during combustion behind an axisymmetric body in a supersonic stream.

Baev, S. Vuititskii, A. Garanin, P. Tret'yakov & V. Yasakov Combustion, Explosion and Shock Waves vol pages – ()Cite this articleAuthor: V.

Baev, S. Vuititskii, A. Garanin, P. Tret'yakov, V. Yasakov. Assessment of turbulence model performance for transonic flow over an axisymmetric bump - Volume Issue - R. Hasan, J. McGuirkCited by: supersonic axisymmetric nonisobaric jet [1 - 6]. They are registered in the form of longitudinal black and white bands on the photographs with long exposure and under visualization of cross-sections of the first barrel a wave-shaped or saw-shaped boundary of a supersonic mixing layer is seen [].

Fig. integration along shocks closing local supersonic regions. This method is more exact then the ordinary method of integration of pressure along the body surface. The efficiency of a numerical algorithm is demonstrated by calculating transonic flow over thin bodies of revolution.

The results concerning calculations of the wave drag of elongate 3-D. Report presenting some experimental and theoretical studies of axisymmetric free jets exhausting from sonic and supersonic nozzles into still air and into supersonic streams as a way to investigate problems associated with propulsive jets.

A variety of variables for each case are considered, including jet Mach number, nozzle divergence angle, jet static-pressure ratio, free-stream Mach Cited by:   In this paper an axisymmetric computational aeroacoustic procedure is developed to investigate the generation mechanism of axisymmetric supersonic jet screech tones.

The axisymmetric Navier-Stokes equations and the two equations standard k-ϵ turbulence model modified by Turpin and Troyes [“Validation of a two-equation turbulence model for axisymmetric reacting and non-reaction Cited by: (Top) Pressure impact map (hPa) of a pure N 2 O free supersonic expansion measured using a Pitot tube (N 2 O slm, p ∞ = Pa, p 0 = hPa).

The horizontal axis corresponds to the jet axis (Z), the dimensions of the sampling grid are indicated, (middle) resulting flow velocity (V S) along the jet axis, and (bottom) resulting Cited by: 6. An Effective method of calculating transonic flows and wave drag of axisymmetric and 3-D elongate bodies within framework of transonic equivalence rule.

A.S. Fonarev1, J.T. Madhani1 and M.A. Naida2 1School of Aerospace, Mechanical and Mechatronic Engineering University of Sydney, NSWAUSTRALIA 2 CIBC,National Support and Consulting.

Buy Transonic Compressor Stages with Non-Axisymmetric End Walls: Unsteady and Steady Performance on FREE SHIPPING on qualified ordersAuthor: Steffen Reising.

But because the flow is non-isentropic, the total pressure downstream of the shock is always less than the total pressure upstream of the shock. There is a loss of total pressure associated with a shock wave. On this web page, we show a method for. For jets exhausting into supersonic streams, an attempt has been made to present primarily theoretical certain jet interference effects and in formulating experimental studies.

The primary variables considered are jet Mach number, free stream Mach number, jet static pressure ratio, ratio of specific heats of the jet, nozzle exit angle, and.

The base pressure behind various shapes of bodies at subsonic and supersonic speeds (projectiles, a fuselage with cut-off trailing end, an airfoil section with thick trailing edge, a two-dimensional section with flat base and sheet metal joints, etc.) depends largely upon the length of the forebody, the ratio of base to body diameter, the.A cm (in.) capture diameter model of a mixed-compression axisymmetric inlet system with a translating cowl was designed and tested.

The internal contours, designed for Mach numberprovided a throat area of 59 percent of the capture area when .Investigations of Supersonic Flow Around a Long Axisymmetric Body M.R. Heidari1;, M.

Farahani2, M.R. Soltani2 and M. Taeibi-Rahni2 Abstract. In this work, a supersonic turbulent ow over a long axisymmetric body was investigated, both experimentally and computationally. The experimental study consisted of a series of wind tunnel tests for theCited by: 1.