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Saturday, July 18, 2020 | History

2 edition of Turbulent-flow separation criteria for overexpanded supersonic nozzles found in the catalog.

Turbulent-flow separation criteria for overexpanded supersonic nozzles

E. Leon Morrisette

Turbulent-flow separation criteria for overexpanded supersonic nozzles

by E. Leon Morrisette

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  • 32 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:
  • Turbulent boundary layer.,
  • Stratified flow.,
  • Supersonic nozzles.

  • Edition Notes

    StatementE. Leon Morisette and Theordore J. Goldberg, Langley Research Center.
    SeriesNASA technical paper ; 1207, NASA technical paper -- 1207.
    ContributionsGoldberg, Theodore J., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., Langley Research Center.
    The Physical Object
    Pagination36 p. :
    Number of Pages36
    ID Numbers
    Open LibraryOL18014161M

    buy numerical simulation of turbulent shock-induced separated flows: application to the supersonic over-expanded nozzle flow on free shipping on qualified orders. Reignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2 gas (GH2) in the film cooling device, particularly when the nozzle operates under over expanded flow conditions at sea level or at low altitudes. Consequently, Cited by: 3.

    An experimental and numerical analysis of a low-angle annular expander nozzle is presented to observe the variance in shock structure within the flow field. A RANS-based axisymmetric numerical model was used to evaluate flow characteristics and the model validated using experimental pressure readings and schlieren images. Results were compared with an equivalent converging-diverging nozzle Cited by: 1. The need to improve nozzle performance under overexpanded conditions and to mitigate the side loads fostered several experimental [1, 2, 3] and numerical investigations [4, 5, 6]. All these studies revealed two distinct separation processes: the free shock separation (FSS), in which the boundary layer separates from the nozzle wall and never Author: Emanuele Martelli, Pietro Paolo Ciottoli, Matteo Bernardini, Francesco Nasuti, Mauro Valorani.

    Unsteady Phenomena in Supersonic Nozzle Flow Separation Dimitri Papamoschou* and Andrew Johnson† University of California, Irvine, Irvine, CA This work considers the instability of the jet plume from an overexpanded, shock-containing convergent-divergent nozzle and attempts to correlate this instability to internal. Abstract; PDF ( K) Figures; Tables; References; Numerical simulation of an over-expanded supersonic and subsonic industrial nozzle flow relevant to flaring system 1. Faisal Al Qurooni, a Ali Vakil, b c Ehab Elsaadawy, d Sheldon I. Green b a Saudi Aramco, South Ghawar Producing Department, Udhailiyah , KSA.. b Department of Mechanical Engineering, The Author: Faisal Anwar Al Qurooni, Ali Vakil, Ehab Elsaadawy, Sheldon I Green.


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Turbulent-flow separation criteria for overexpanded supersonic nozzles by E. Leon Morrisette Download PDF EPUB FB2

A comprehensive compilation of available turbulent-flow separation data for over-expanded supersonic nozzles is presented with a discussion of correlation techniques and prediction methods. Data are grouped by nozzle types: conical, contoured, and two-dimensional wedge.

Correlation of conical-nozzle separation is found to be independentFile Size: 1MB. A comprehensive compilation of available turbulent flow separation data for overexpanded supersonic nozzles is presented with a discussion of correlation techniques, and prediction methods.

Data are grouped by nozzle types: conical, contoured, and two dimensional by: Turbulent-flow separation criteria for overexpanded supersonic nozzles / By E. Leon. Morrisette, joint author. Theodore J.

Goldberg, Langley Research Center. and United States. National Aeronautics and Space Administration. Scientific. We present experimental results on separation of supersonic flow inside a convergent–divergent (CD) nozzle.

Goldberg, T.J.: Turbulent flow separation criteria for overexpanded supersonic nozzle. NASA TP () Google Scholar. D., Johnson, A.: Unsteady phenomena in supersonic nozzle flow separation.

AIAA Paper ( Cited by: Numerical investigation of flow separation behavior in an over-expanded annular conical aerospike nozzle Chinese Journal of Aeronautics, Vol. 28, No. 4 Numerical study of shock/boundary layer interaction in supersonic overexpanded nozzlesCited by: Flow Separation in Rocket Nozzles, a Simple Criteria Ralf H.

Stark* German Aerospace Center, Lampoldshausen,DGermany Cold and hot flow tests were conducted to investigate theflow separation in rocket nozzles. The esults are presented. A separatior n data base includinga wide range of. Supersonic flow separation in planar nozzles 29 July | Shock Waves, Vol.

19, No. 3 Experimental and Numerical Study of Jet Mixing from a Shock-Containing NozzleCited by: A comprehensive, up-to-date review of supersonic flow separation and side-loads in internal nozzle flows is given with an in-depth discussion of different approaches for predicting the phenomena.

This includes methods for predicting shock-induced separation, models for predicting side-load levels and aeroelastic coupling effects. Additionally, some design criteria for modern thrust optimized nozzles according to these effects are proposed.

Keywords: launcher nozzle, TOC, TIC, conical contour, overexpanded regime, free, restricted shock separation. INTRODUCTION The nozzle, an end-element of the propulsive process cycle, represents a critical part of any aerospace vehicle.

Braun’s point of view the flow separation in rocket nozzles leads, due to the cavitation effect, to a corrosive damage of the nozzle.

A flow separation criter ion is no t establis h : Ralf Stark. Separation of supersonic flow in convergent–divergent nozzles is investigated by solving the Reynolds-averaged Navier–Stokes equations with a two-equation k-ω turbulence model.

Keywords Nozzle flow separation Overexpanded nozzle Free Shock Separation (FSS) Restricted Shock Separation (RSS) Cap-shock patternAuthor: K. Sreejith, M. Dhrishit, M. Deepu, T. Jayachandran. Turbulent-flow separation criteria for overexpanded supersonic nozzles. [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.

Boundary-Layer Separation in Supersonic PropellingNozzles studied two-dimensionally for both laminar and turbulent flow, as have incident shocks on flat plates. so some considerable distance after separation.

Overexpanded nozzles and 'sufficiently large' steps are cited as possible examples, while other systems such as incident shocks. The past decade has seen a qualitative advancement of our understanding of physical phenomena involved in flow separation in supersonic nozzles; in particular, the problem of side loads due to asymmetrical pressure loads, which constitutes a major restraint in the design of nozzles for satellite by: This separation phenomenon can also appear in overexpanded nozzle flow at a fixed nozzle pressure ratio (NPR), where NPR=pc/pa (pc and pa are respectively the chamber and the ambient pressure).

The flow issued from the toc nozzle exhibits two different kinds of separation patterns for a certain range of pressure : Abderrahmane Nebbache. Supersonic nozzle flow separation is a flow phenomenon that occurs under a specific nozzle pressure ratio (NPR) [1].

The research work on nozzle flow separation began in the s. Three separation criteria are plotted for comparison: the well-known Schmucker criterion 50 (1), the separation criterion (2) for turbulent nozzle flows suggested by Stark et al, 52, and the separation criterion (3) suggested by Ge et al.

53 recently based on flow separation data in asymmetric ramp by: 5. Turbulent-flow separation criteria for overexpanded supersonic nozzles / ([Washington]: National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va.: For sale by the National Technical Information Service, ), by E.

Leon Morrisette, Theodore J. Goldberg, Langley Research Center, and United. Papamoschou et al. Fig. 1 Primary jet flow at Mach surrounded by an annular secon- dary flow at nozzle pressure ratio NPR = a Secondary nozzle is convergent, b secondary nozzle is convergent–divergent Fig.

2 Sketch of shock structure and fluid phenomena for overexpan- ded nozzle. a Inviscid case, b viscous (separated) case There is a large volume of literature. Experimental Separation Criteria Theoretical Calculation of the Separation 36 39 Overview of the Most Important Flow Separation 39 Theories for Rocket Nozzles Separation Theory of L.

Crocco and R. Probstein [8] 40 References 44 Appendix: Prediction of Separation for the Space Shuttle 48 Main Engine iiiCited by: 9. nozzles with conical sections like those used in practical high-speed propulsion applications. LES simulations and experimental measurements in the form of PIV and shadowgraph imaging and far-field acoustic measurement are employed.

The development of the supersonic jets from these nozzles are examined in underexpanded, perfectly expanded and.nozzle, the rocket engine, the structure and the payload. The launcher on of the predicti separation position is crucial for rocket engine design and determines the maximum possible nozzle area ratio, a deciding factor for the engine performance.

The separation characteristics of nozzles under sea-level conditions can be easily studied. TheFile Size: 99KB. Accurate simulation of the noise generated by a hot supersonic jet including turbulence tripping and nonlinear acoustic propagation “ Turbulent-flow Separation Criteria for Overexpanded Supersonic Nozzles,” Technical Paper No.

(NASA “ An analysis of the correlations between the turbulent flow and the sound pressure field of Cited by: 6.