3 edition of **A Numerical Investigation of Subsonic and Supersonic Flow Around Axisymmetric Bodies** found in the catalog.

A Numerical Investigation of Subsonic and Supersonic Flow Around Axisymmetric Bodies

- 344 Want to read
- 25 Currently reading

Published
**2001** by Storming Media .

Written in English

- SCI085000

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

Format | Spiral-bound |

ID Numbers | |

Open Library | OL11849352M |

ISBN 10 | 1423550188 |

ISBN 10 | 9781423550181 |

A numerical approach based on multiblock, multigrid, local refinement and preconditioning methods has been developed to solve the incompressible Reynolds-averaged Navier-Stokes (RANS) equations. Three-dimensional flow computations for axisymmetric bodies at angles of attack and yaw with and without. Sixth International Conference on Numerical Methods in Fluid Dynamics Numerical study of nonlinear axisymmetric flow of fluid between two concentric rotating spheres. Pages Astaf'eva, N. M. (et al.) Supersonic flow of viscous gas around bodies and the flaw in the wake (methods of a numerical solution and computing results). tion zones.1 There have been several axisymmetric numerical studies for cylinders with height-to-radius aspect ratios =H/R ,,2–6 where H and R are the height and radius of the cylinder. A close examination of the linear sta-bility results of Ref. 7 shows that in this aspect ratio range, where the steady basic state loses stability to. The numerical analysis also includes the numerical flow visualization and comparison with the available experimental data. The key concern of research into the area of protruding spikes ahead of blunt bodies is the unstable flow that has been observed to exist for particular families of blunt bodies in supersonic and hypersonic : R. C. Mehta.

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ARMY RESEARCH LABORATORY A Numerical Investigation of Subsonic and Supersonic Flow Around Axisymmetric Bodies by George D.

Catalano and Walter B. Sturek, Sr. A DESCRIPTION OF NUMERICAL METHODS AND COMPUTER PROGRAMS FOR TWO-DIMENSIONAL AND AXISYMMETRIC SUPERSONIC FLOW OVER BLUNT-NOSED AND F!LA€BD BODIES By Mamoru Inouye, John V.

Rakich, and Harvard Lomax Ames Research Center SUMMARY The computer programs developed at Ames Research Center for calculating. 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. The aim of this study is to determine the supersonic flow parameters around the axisymmetric cone body by finite volume methods.

A code is written to capture the oblique shock wave behind a cone placed in supersonic free by: 1. A supersonic turbulent flow over a long axisymmetric body was investigated both experimentally and computationally.

The experimental study consisted of a series of wind tunnel tests for the flow over an ogive-cylinder body at Mach number of and at angles of attack between Cited by: 1. A time-dependent numerical method for calculating supersonic flow about blunt bodies at large angles of attack is presented.

The axisymmetric bodies with sharp shoul- ders which are treated are constructed with a generator composed of segments of constant curvature.

The nonaxisymmetric bodies have continuous slope and curvature. All flow. CALCULATION OF AXISYMMETRIC SUPERSONIC FLOW PAST BLUNT BODIES WITH SONIC CORNERS, INCLUDING A PROGRAM DESCRIPTION AND LISTING By Jerry C.

South, Jr. Langley Research Center SUMMARY A program for the approximate calculation of supersonic flow of an ideal gas past blunt bodies with sonic corners is described. Numerical solutions are File Size: 2MB. The results of an experimental investigation of supersonic Mach flow past an axisymmetric cylindrical model body with a rectangular annular cut-out on its lateral surface are presented.

The effect of angles of attack in the interval 0 ≦α ≦40° on the flow pattern and the aerodynamic characteristics of a body of power-law shape (equation of the generator in the cylindrical coordinate system r=z n, n=) is investigated for supersonic flow without injection and with intense subsonic localized injection from the a result of numerical Cited by: 4.

Masson and T. Taylor, “A numerical solution of supersonic flow past blunt bodies with large mass injection,” Fluid Dynamics Trans., 5, pt 1 (). Google Scholar Cited by: 1. Keywords: axisymmetric, supersonic flow, cone body, finite volume, oblique shock wave.

1 Introduction A numerical technique is proposed to predict a supersonic flow around an axisymmetric cone body.

An explicit formulation with the finite volume method Computational Methods and Experimental Measurements XIV OVER AXISYMMETRIC BODIES IN SUPERSONIC FLOW by B. TYLER BROOKER SEMIH M. OLCMEN, COMMITTEE CHAIR JOHN BAKER KEITH A. WILLIAMS A THESIS Submitted in partial fulfillment of the requirements for the degree of Master of Science in Aerospace Engineering and Mechanics in the Department of Aerospace Engineering and Mechanics in File Size: 2MB.

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, Cited by: axisymmetric bodies, with an emphasis on transition characteristics near the leeward line of symmetry.

Transition in boundary layers on axisymmetric bodies in supersonic flow has been extensively studied in the literature. Particularly noteworthy in this context are the tests on a common 5-degree half-angle cone model at zeroCited by: 4. Page breaks are true to the original; line EXPERIMENTAL AND NUMERICAL INVESTIGATION OF THE UNSTEADY FLOW AROUND A PROPELLER Experimental and Numerical Investigation of the Unsteady Flow around a Propeller to, ore, Felice, to (Istituto Nazionale per Studi ed Esperienze di Architettura Navale, Italy), o.

Numerical Investigation of Diaphragm Mass and Viscous Effects aligned with a supersonic flow from the left.

There is initially no flow inside the intake, where the pressure is low, and the outside subsonic flow inside starting shock diaphragm x. It is quite evident from these available literatures that the most of these previous numerical works were mainly directed towards the investigation of mean flow field successfully, while a little attention was given to the evolution of flow structures in the wake region of the cylindrical after body placed in supersonic by: 9.

Numerical investigations of the aerodynamic characteristics and the flows around slender axisymmetric bodies in wide parameters range: M∞=0.÷, α=0°÷° are considered. Various numerical, theoretical and engineering methods are applied to calculate aerodynamic characteristics of two buster Size: 1MB.

subsonic flow characteristics of an axisymmetric hill immersed in a boundary layer. Reynolds number is a factor in the flow around wall-mounted hills; Hunt et. [1] show that re-attachment of the separated flow downstream. The separated flow over a cylinder elongated by another cylinder of a smaller diameter is investigated numerically at the high subsonic regime using zonal detached eddy simulation (ZDES) and compared with the experimental data of Deprés, Reijasse, and Dussauge [AIAA J.

42, ()].First, it is shown that this axisymmetric step flow has much in Cited by: Experimental study of supersonic axisymmetric base flow. The investigation showed that the drag of a cavity with closed flow was substantially higher than that of a cavity with open flow and this kind of passive control can be employed to control cavity flow field at supersonic speed.

This kind of information will be valuable for an Author: Gamal H. Moustafa, D. Bisht, Rajan, E. Rathakrishnan. 1Corresponding author: Email: [email protected] Proceedings of the 1st National Aerospace Propulsion Conference NAPC March, IIT Kanpur, Kanpur NAPC Numerical investigation of axisymmetric underexpanded supersonic jets.

Experimental investigation of axisymmetric hypersonic shock-wave/turbulent-boundary-layer interactions - Volume - N. Murray, R.

Hillier, S. WilliamsCited by: On this web page, we show a method for determining the supersonic flow past a cone. The method was first developed by G.I. Taylor and J.W. Maccoll in The derivation of the differential equation shown on the slide is fairly complicated.

The method assumes that the supersonic flow along a cone is simplified because of symmetry considerations. Numerical investigation of the flow structures in a quasi-axisymmetric scramjet engine K. Tanimizu1, T. Jones1, H. Ogawa1, and A. Pudsey1 1School of Engineering, RMIT University, Melbourne, VictoriaAustralia Abstract The flowfield characteristics of a relatively small quasi-axisymmetric scramjet vehicle at a Mach 6 flight condition have.

EFFICIENT NUMERICAL METHOD FOR SIMULATION OF SUPERSONIC VISCOUS FLOW PAST A BLUNTED BODY AT A SMALL ANGLE OF ATTACK G. TmsKn, S. UTYUZHNIKOV~ and N. YAMALEEV Department of Computational Mathematics, Moscow Institute of Physics & Technology, Dolgoprudny, MoscowRussia. The reference Reynolds number is.

Re ref = a ref X ref / (nu) ref = E+06 where a ref is the speed-of-sound and (nu) ref is the kinematic viscosity using conditions at the nozzle inflow total pressure and temperature. The reference length is X ref = ft. The Reunolds number based on the nozzle exit velocity and radius, u e = ft/sec and r e = in is.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA A fixed-length Boundary Element Method (BEM) is used to investigate the super- and partial cavitating flows around various axisymmetric bodies using simple and reentrant jet models at the closure zone of cavity.

Also, a simple algorithm is proposed to model the quasi-3D cavitating flows over elliptical-head bodies using the axisymmetric by: 3. AeroCFD is a "true" three-dimensional axisymmetric and two-dimensional implicit finite volume CFD program that solves the inviscid Euler equations for subsonic, transonic and supersonic flow using automatic mesh generation and graphical results visualization.

AeroCFD provides a maximum of cells in the axial direction, 50 cells in the transverse direction and 10 cells in. A numerical analysis was conducted to investigate the inlet buzz and combustion oscillation in an axisymmetric ramjet engine with wedge-type flame holders.

The physical model of concern includes the entire engine flow path, extending from theFile Size: 2MB. 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 Cited by: Equation () is a valid approximation for small perturbations in subsonic or supersonic ﬂow. For 2-D ﬂows over planar bodies it is sufﬁcient to retain only the ﬁrst term in () and we use the expression.

() For 3-D ﬂows over slender approximately axisymmetric bodies we must retain the last term and so. () P P' 1 File Size: 2MB. axisymmetric acoustic problems in a subsonic uniform flow Bassem Barhoumi Acoustics Group. hal Boundary Element Method Formulation for axisymmetric acoustic problems in a subsonic Abstract This paper presents a new analysis method and numerical development of the direct boundary element method formulation for Cited by: 2.

Experimental Investigations on the Characteristics of Supersonic Flow past Axisymmetric AFT Ramp Cavities Jeyakumar S, Surjith N, Venkateshwaran V, Karkuvelraja A, Samy G.S, Jaganathan K.D supersonic. Since the flow is subsonic, the shear layer is quite unstable and it quickly rolls up to form a : Jeyakumar S, Surjith N, Venkateshwaran, Karkuvelraja A, Samy G.S, Jaganathan K.D.

Experimental and numerical investigation of an axisymmetric freejet vector is normal to the plane of the flow; for an axisymmetric jet, however, as the jet spreads rings and vortices are stretched.

To make numerical predictions of the flow field using the finite volume technique and k-E turbulence model, and (4) To compare the predicted. The flow noise of a sonar platform is one of the main background interferences for sonar applications. This paper focuses on the flow noise of an axisymmetric body in a complex oceanic environment.

Under the condition of a constant stream velocity which comes from the axial direction, an analytical method for computing the flow noise power spectrum in the transition Author: Chunlong Huang, Kunde Yang, Hui Li, Yukun Zhang.

paradox type in the axisymmetric flows with the Mach disc and features of variation of flow parameters behind it are analogous to those of the work Ivanov et al. () for the steady reflection of wedge-generated shock wave with forming a Mach stem in two-dimensional supersonic flow at M ==5/3, wedge angle δw= File Size: 3MB.

EFFECT OF GEOMETRIC DISTORTION ON THE FLOW FIELD AND PERFORMANCE OF AN AXISYMMETRIC SUPERSONIC INTAKE MOHAMMAD FARAHANI1a, ALIREZA FAZLOLLAHI-GHOMSHIb, AND MOHAMMAD BADRGOLTAPPE c abcSharif University of Technology ABSTRACT Supersonic intakes are designed and used for reducing the speed of inlet air to.

Flow Investigation of an Axisymmetric Single and Multi Jets Padmalochini. The axisymmetric nozzle is modelled and meshed using Gambit. The boundary conditions are specified and jet plume structure is Analysis of Twin Jet Supersonic Flow with Fluent Software”.

• The coordinates are then plotted in gambit and 2-D. () Viscous-inviscid interactions on axisymmetric bodies of revolution in supersonic flow.

Journal of Fluid Mechanics 1, () Transonic flow past a Cited by: 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.The basic hypothesis in the present flow model is presented in figure 1.

The flow is divided into the following regions: (1) Inviscid flow around the corrected body. (2) Viscous flow: (a) Upstream of base, the boundary layer calculation is made on the solid boundaries of the model (for cases with no separation boattail).