3 edition of **Two-dimensional nozzle plume characteristics** found in the catalog.

Two-dimensional nozzle plume characteristics

U. Von Glahn

- 111 Want to read
- 10 Currently reading

Published
**1987** by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC, Springfield, Va .

Written in English

- Aerodynamics.,
- Nozzles.

**Edition Notes**

Other titles | Two dimensional nozzle plume characteristics. |

Statement | Uwe H. von Glahn. |

Series | NASA technical memorandum -- 89812. |

Contributions | United States. National Aeronautics and Space Administration. |

The Physical Object | |
---|---|

Format | Microfiche |

Pagination | 1 v. |

ID Numbers | |

Open Library | OL17660538M |

A new method of designing two-dimensional laval nozzles for a parallel and uniform jet [Foelsch, Kuno] on *FREE* shipping on qualifying offers. A new method of designing two-dimensional laval nozzles for a parallel and uniform jetAuthor: Kuno Foelsch. The parameter distribution in the single-nozzle engine obtained by different chemical reaction mechanisms is shown in Figure 8; similar plume flow field structure and the same number of shock waves can be obtained by methods of single-step chemical reaction and multistep chemical reaction, but the length of exhaust plume of the former is 8 m. Cavitation in Two-Dimensional Asymmetric Nozzles Diesel fuel spray characteristics are thought to depend on cavitation inside the fuel injector nozzles. These nozzles are very small and the fuel flow is very fast, making experimental observation very by: @article{osti_, title = {Design an efficient air impingement nozzle array}, author = {Steinberg, N I}, abstractNote = {Direct air impingement is the most commonly used system for heating, cooling,and drying webs and films. Air impingement heat-transfer systems blow jets of air (or other gas) perpendicular to the web from an array of nozzles.

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Plume characteristics of two-dimensional nozzles without ejectors. Included in the study are the effects of nozzle aspect ratio and flow conditions including jet Mach number and temperature on the plume decay and spreading of two-dimensional nozzles. Correlation procedures including these variables are developed in a manner similar toFile Size: 1MB.

Get this from a library. Two-dimensional nozzle plume characteristics. [Uwe H Von Glahn; United States. National Aeronautics and Space Administration.].

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Secondary stream and excitation effects on two-dimensional nozzle plume characteristics.

UWE VON GLAHN. Abstract. Future high performance aircraft will likely feature asymmetric or two-dimensional nozzles with or without ejectors. In order to design two-dimensional nozzle/ejector systems of minimum size and weight, the plume decay and spreading characteristics of basic two-dimensional nozzles Author: Uwe H.

Vonglahn. In order to design two-dimensional nozzle/ejector systems of minimum size and weight, the plume decay and spreading characteristics of basic two-dimensional nozzles must first be : Uwe H. Von Glahn. Secondary stream and excitation effects on two-dimensional nozzle plume characteristics.

By Uwe H. Von Glahn. Abstract. In order to design two-dimensional nozzle/ejector systems for future high performance aircraft, the basic engine exhaust plume velocity and temperature decay as effected by the secondary stream (ejector) and decay Author: Uwe H.

Von Glahn. Secondary stream and excitation effects on two-dimensional nozzle plume characteristics. By Uwe H. Vonglahn.

Abstract. In order to design two-dimensional nozzle/ejector systems for future high performance aircraft, the basic engine exhaust plume velocity and temperature decay as effected by the secondary stream (ejector) and decay augmentation Author: Uwe H.

Vonglahn. Two phase plume dynamics - A comparison of axisymmetric and three dimensional simulations. Mark Two-dimensional nozzle plume characteristics book, Brady Brown, Jacob Krispin, James Collins and Ralph Ferguson. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by: 7.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA A schematic sketch of the typical two- dimensional nozzle plume centerline decay with axial distance is shown in Fig. 4, together with that for a conic (or square) nozzle plume.

It is apparent that with equal flow conditions the two- dimensional nozzle velocity decay is initiated sooner (closer to the nozzle exit) than that of the conic nozzle. Preliminary numerical simulation using a Direct Simulation Monte Carlo (DSMC) method was conducted to elucidate the internal flowfield and external plume characteristics of micro-single-nozzles and micro-nozzle-arrays, since these small-sized nozzles generally undergo a severe viscous loss due to the Two-dimensional nozzle plume characteristics book Reynolds by: Get this from a library.

Secondary stream and excitation effects on two-dimensional nozzle plume characteristics. [Uwe H Von Glahn; United States. National Aeronautics and Space Administration.].

If the surface is stationary, the preferred nozzle is usually some type of full cone nozzle, since its pattern will cover a larger area than the other styles. Spatial applications, in which the objective is not primarily to spray onto a surface, are more likely to require specialized spray characteristics.

named by Minimum Length Nozzle (MLN) with curved sonic line. Both types exist for two-dimensional and axisymetric flows resulting in four possible configurations. The MLN with right sonic line [1,2,7,8,10]. [3] studied the MLN axisymmetric with right sonic line.

[5] presents the first complete analysis of the two-dimensional curved sonic line Size: KB. A two dimensional convergent-divergent nozzle with a rectangu-lar cross section is modelled under ambient conditions experienced by a supersonic jet engine at cruising altitude.

Instability due to shock wave formation at the divergent section of the nozzle and Mach shocks downstream of the jet plume region are investigated.

The noz-zle:pressure Cited by: 5. For ideal nozzles, basically two different types of shock structures in the plume may appear for overexpanded flow conditions, a regular shock reflection or a Mach reflection at the nozzle centreline.

There are two categories for this nozzle according to the sonic line. If the sonic line is a straight line, the wall Corresponding :+ £-mai7aMress:[email protected] at the throat generates a centered and divergent expansion waves.

The second category has a curved sonic by: The two-dimensional nozzle was divided into two sections, as shown in Panel (a) of Fig. S1 (sac 1) represents the straight channel section and S2 (sac 2) shows the step hole section, respectively.

To extract the bubble and liquid phases in the nozzle, a 60%-pixel intensity threshold was used. Scarf angles between î² = 30 to the expansion ratios of the scarfed nozzle configurations were between îµ = 90 and the scarfed nozzle plumes were investigated in the HAMBURG vaccum test facility using heat and force sensors, witness plates, QCM and plume by: 2.

#!&#*+$. /-,0#%. 1 23!,(&4-+. #+!+'. 5'6+. 7#%.8. 9,(:6%. /,($%. 6% -?6&(. 8'(,[email protected] #)+. 5 (,@. 5 #,!bbc!b%!-))-&+d. +'(8. #&++. #+!5'6. Critical flowmetering: The characteristics of cylindrical nozzles with sharp upstream edges.

Abstract. A detailed study of the influence of axial length on the critical discharge coefficient of cylindrical orifices with sharp upstream edges is by: Supersonic Two-Dimensional Plug Nozzle Design at High Temperature. Application for Air.

The method of characteristics is used with a new form of the Prandtl Meyer function at high temperature. The influence of external flow on the plume physics of cell nozzle flows and the cell base wake behavior of simplified clustered linear aerospike nozzles were characterized using surface pressure.

Experimental Procedures. An experimental system was established, including gas supply, flow meter, combustor, various double S-shaped nozzles, and data acquiring instruments, to acquire the nozzle wall pressure distributions (shown in Figure 4) and infrared radiation of airflow which was supplied by an electrical single-stage compressor was heated in a combustor with aviation by: 1.

The upstream width of the nozzle was 15 mm, the length of the nozzle was 10 mm with a width of 2 mm. Other details of the two-dimensional nozzle can be found elsewhere [11, 12].

A xenon lamp. 2D Method of Characteristics Tool was funded to investigate performance and operating characteristics of the GTX rocket nozzle exhaust system. dimensional objects. By using streamlines from a known flowfield, such as a two- dimensional or conical flow, complex three-dimensional shapes can be traced.

File Size: 2MB. It uses the classic Method of Characteristics (MOC) technique to design a jet nozzle and analzye the internal flow field, the plume, and the external flow near the nozzle exit. It can then determinine the interactions between these three flow fields. We are making it available for beta testing among the nozzle.

In this investigation, a transparent two-dimensional nozzle was utilized for high-speed shadowgraph visualization and flash boiling sprays at various fuel temperatures (superheat degrees) were. The length of the nozzles (throat to exit) is ft, and the nozzles are gimbaled outward by an angle of deg.

A conical fairing approximately ft long extends from the rocket body into the base region to divert external airflow away from the Size: KB. RECTANGULAR NOZZLE PLUME VELOCITY MODELING FOR USE IN JET NOISE PREDICTION U.H.

von Glahn National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio Abstract A modeling technique for predicting the axial and transverse velocity characteristics of rectangu- lar nozzle plumes is Size: 1MB.

Method of Characteristics: Two-Dimensional Steady Flow So far, we have only dealt with flows that are one-dimensional (Chapters ) or are comprised of simple two-dimensional elements such as oblique shocks or Prandtl-Meyer expansion fans (Chapters ). For more complex flows.

Experimental characterization of two-dimensional spot profiles for two proton pencil beam scanning nozzles. Liyong Lin, Christopher G Ainsley, Timothy D Solberg and James E McDonough. Published 20 January • Institute of Physics and Engineering in Medicine Physics in Medicine & Biology, Vol Number 2Cited by: Nozzle is a one-dimensional and two-dimensional, compressible flow computer program for the analysis of converging-diverging nozzles.

Nozzle models inviscid, adiabatic and hence isentropic flow of a calorically perfect gas through variable-area ducts. Nozzle internal flow may be entirely subsonic, entirely supersonic or a combination of subsonic and supersonic including shock waves in the.

Abstract We investigate the planar jet from an two-dimensional nozzle with asymmetry in lip lengths. Experiments are conducted at Re =, The aspect ratio of the nozzle exit is fixed towhich is sufficiently large to obtain two-dimensional well-developed turbulent jet.

The lip length l. the nozzle, throat, and combustion chamber of the engine; the FPI spectrometer A discussion regarding SSME plume characteristics can be found in reference The radiant power and line widths of spectral 12 and the Two Dimensional Kinetics (TDK) _ computer codes.

During engine start, the SSME nozzle undergoes significant mechanical File Size: 1MB. Using method of characteristics, design a two-dimensional minimum length nozzle. For exit Mach number Plot the contour of the nozzle on a graph with equal axes. You have to use 7 expansion waves at the start of the supersonic region.

Using method of characteristics, design a two-dimensional minimum length nozzle. For exit. Mach number M= Plot the contour of the nozzle on a graph with equal axes. 7 expansion waves must be used at the start of the supersonic region. Please show all your work including any computer programs you used for the solution.

Using method of characteristics, design a two-dimensional minimum length nozzle. For exit Mach number check the Exit_Mach_Numbers= Plot the contour of the nozzle on a graph with equal axes. You have to use 7 expansion waves at the start of the supersonic region.

Question: Using The Method Of Characteristics, Compute And Graph To Scale, The Contour (using Solid Lines) And The Characteristics (using Dashed Lines) Of A Two-dimensional Minimum-length Nozzle For The Expansion Of Air To A Design Exit Mach Number Of 3. Assume The Specific Heat Ratio Is For Clarity, Lay Out The Design Using A Schematic, Number The Intersection.The starting process of two-dimensional nozzle flows has been simulated with Euler, laminar and k - g two-equation turbulence Navier-Stokes equations.

The flow solver is based on a combination of LUSGS subiteration implicit method and five spatial discretized schemes, which are Roe, HLLE, MHLLE upwind schemes and AUSM+, AUSMPW schemes. In the paper, special attention is for the flow.accelerating nozzle flow does not permit time for the gas to reach full chemical equilibrium.

A considerable number of numerical analysis has been undertaken to investigate these loss mechanisms and to overcome these losses. Method of Characteristics (MOC) is a computational procedure used to compute and simulate the two-dimensional nozzles.