3 edition of **Transient, hypervelocity flow in an axisymmetric nozzle** found in the catalog.

Transient, hypervelocity flow in an axisymmetric nozzle

Peter A. Jacobs

- 335 Want to read
- 24 Currently reading

Published
**1991**
by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va
.

Written in English

- Nozzles.,
- Unsteady flow (Aerodynamics)

**Edition Notes**

Statement | P.A. Jacobs. |

Series | ICASE report -- no. 91-1., NASA contractor report -- 187496., NASA contractor report -- NASA CR-187496. |

Contributions | Langley Research Center. |

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

Format | Microform |

Pagination | 1 v. |

ID Numbers | |

Open Library | OL15388659M |

A nozzle capable of deflecting both up and down as well as right and left is a 3D nozzle. To date, only a handful of aircraft have made use of 2D or 3D thrust vectoring nozzles. Probably the most well known of these are the American F Raptor and Russian Su, both employing 2D nozzles for improved maneuverability in pitch. through an axisymmetric convergent nozzle have been theoretically and experimentally explored. Choking criteria of a convergent nozzle flow are proposed from experiment and theory. A nozzle of a variable length from the inlet to exit has been used for the purpose of .

From Introduction: "A method for the design of three-dimensional nozzles based on axi-symmetric flow is presented in this paper. The design method presented in this paper is general; however, as an illustrative example of the design of a Mach number 10 nozzle with square test section is included.". Computational fluid dynamics analyses of an axisymmetric nozzle at transonic free stream conditions have been adiabatic problem had taken by his book fundamental of compressible flow. Shames [3] discussed the fluid behavior in Figure Velocity vectors of the flow nozzle Figure Turbulent kinetic energy contour of nozzle (tail region).

Mach number contours for supersonic axisymmetric nozzle jet flow. Introduction. This study is an example study demonstrating the use of Wind-US to compute axisymmetric, nozzle flow fields. Download File. All of the files associated with this study are available in the compressed tar file The files can then be accessed by the. This report presents a method to design the inviscid wall contour of a supersonic, axisymmetric nozzle producing uniform parallel flow at the exit. The calculation methods used are restricted to a perfect gas. The axis velocity distribution must be specified. A complete flow pattern within the nozzle is computed by the method of characteristics beginning at Mach on the axis and extending.

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Get this from a library. Transient, hypervelocity flow in an axisymmetric nozzle. [P A Jacobs; Langley Research Center.]. Transient, hypervelocity flow in an axisymmetric nozzle.

By Hypervelocity flow in an axisymmetric nozzle book. Jacobs. Abstract. The performance of an axisymmetric nozzle designed to produce uniform parallel flow with a nominal Mach number of 8 is examined.

The nozzle employs a flow decoupling approach and is calibrated by measuring Pitot pressures near the exit plane for a number of Author: P.

Jacobs. The transient flow in a long cylindrical pipe caused by the motion of a valve is a subject of significant interest in wide engineering applications. Despite the partial success of existing theoretical models in explaining certain transient flow phenomena, they can hardly predict the evolution of strong water hammer, in particular the one Author: Lijun Xuan, Feng Mao, Jiezhi Wu, Jiezhi Wu.

Axisymmetric describes the rotational symmetry referring to an object being symmetrical and cylindrical on an axis. For example, a cone. FLUENT - Compressible Flow in a Nozzle- Step 1. Skip to end of metadata. Created by Disabled Account [email protected], Since the nozzle has a circular cross-section, it's reasonable to assume that the flow is axisymmetric.

So the geometry to be created is two-dimensional. Start GAMBIT. Several numerical simulations of the transient flow of helium is an expansion tube are presented in an effort to identify some of the basic mechanisms which cause the noisy test flows seen in experiments.

The calculations were performed with an axisymmetric Navier-Stokes code based on a finite-volume formulation and upwinding techniques. Abstract. The starting process of two-dimensional and axisymmetric nozzle flows has been investigated numerically.

Special attention has been paid to the early phase of the starting process and to the appearance of a strong secondary shock wave. For both cases, shock intensities and velocities are obtained and discussed. The flow evolution in the Transient case is proved to be more complex.

This page goes through the geometry steps for the Compressible Flow in a Nozzle in the SpaceClaim geometry engine included with ANSYS Workbench.

see this page. We will use the axisymmetric option in FLUENT. This solves the governing equations in the cylindrical coordinate system with no dependence on the circumferential coordinate. In physics and engineering, fluid dynamics is a subdiscipline of fluid mechanics that describes the flow of fluids—liquids and has several subdisciplines, including aerodynamics (the study of air and other gases in motion) and hydrodynamics (the study of liquids in motion).

Fluid dynamics has a wide range of applications, including calculating forces and moments on aircraft. Hypervelocity flow in axisymmetric nozzles design of axisymmetric supersonic nozzles for use in reflected-mode shock tunnels is described. This method has been used to design a moderate Mach number (M = 4) nozzle and a high Mach number (M = 10) nozzle.

Both nozzles have been calibrated by measuring the pitot profiles near the nozzle exit. 2D planar flow is the flow assumed to flow only in a single plane with varying property at different points.

Whereas, axisymmetric flow is also a 2D flow with a line of symmetry along the plane. Lets assume the flow in a pipe which is obviousl. Governing Equations For an axisymmetric flow (with y as the radial coordinate), the finite-volume formulation of the Navier-Stokes equations may be expressed as lfs d(U)dt +1 (yF-yFv)dy tT (yG-yGv)dx =Q', (1) where () indicates a volume average, f~' is the volume per radian and S is a contour in the (x, y)-plane around the volume.

Axisymmetric nozzle design using the MOC Will James: Main CFD Forum: axisymmetric nozzle analysis Marcos: CFX: 3: October 8, axisymmetric nozzle Dmitry: CFX: 2: September 5, Test for a laminar flow in axisymmetric nozzle Victor: Main CFD Forum: 0: Novem compressible flow in a.

1(7 3- Analytical and Experimental Study of Axisymmetric Truncated Plug Nozzle Flow Fields CASE FILE f*O Thomas J.

Mueller, W^ne P^ule, Arthur E. Fanning, Thomas V. Giel and Fred L. Galanga Final Report UNDAS TNFR September, Prepared under Contract No. NAS by UNIVERSITY OF NOTRE DAME NOTRE DAME, INDIANA for. 2 Nomenclature At = nominal nozzle throat area, in2 Ae = nominal nozzle exit area, in2 (See Table 1 Cd,prim = discharge coefficient of primary nozzle, w p + w s w i,p CD = Convergent-Divergent CFD = Computational Fluid Dynamics Cf,g sys = system resultant thrust ratio, F r F i,p + F i,s DTN = Dual Throat Nozzle d1 = upstream throat diameter, in (see Figure 6 and Table 1).

I am investigating annular inlet nozzles for different compressible flow regimes. For simplicity I am using a 2d axisymmetric approach.

But for different geometries that I tried, the nozzle chokes at much lower massflows (%) than it should be (ideal gas). The flow in a conical nozzle is examined experimentally for a range of hypervelocity conditions in a free-piston shock tunnel. The pitot pressure levels compare reasonably well with an inviscid.

The flow of a fluid is transient or unsteady if its flow parameters (i.e. velocity and pressure) are dependent not only on the position in the coordinate system used to describe the field of flow, but also on time.A distinction is made between three different types of transient flow phenomena.

Transient flow phenomena. Stochastically irregular phenomena, e. turbulent fluctuations (see Fluid. transient flow prediction.

• Define a transient boundary condition using a user-defined function (UDF). • Use dynamic mesh adaption for both steady-state and transient flows. • Calculate a transient solution using the second-order implicit transient formulation and the density-based implicit solver. design of in-line edge scarfing nozzles by numerical analysis, using a 2D axisymmetric flow model, and species transport combustion model.

The heat from the combustion gas to preheat oxygen was found to be important. Luo et al modeled transient SEN temperature distributions in “combustion” and “fan type” preheating modes. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA @article{osti_, title = {Effect of nozzle configuration on transport in the stagnation zone of axisymmetric, impinging free-surface liquid jets: Part 1-turbulent flow structure}, author = {Stevens, J and Pan, Y and Webb, B W}, abstractNote = {This study characterized the mean and fluctuating parts of the radial component of the local velocity in the stagnation region of an impinging.