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Thursday, July 30, 2020 | History

3 edition of Numerical simulations of supersonic flow through oscillating cascade sections found in the catalog.

Numerical simulations of supersonic flow through oscillating cascade sections

Numerical simulations of supersonic flow through oscillating cascade sections

  • 246 Want to read
  • 15 Currently reading

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

    Subjects:
  • Aerodynamics, Supersonic.

  • Edition Notes

    StatementDennis L. Huff and T.S.R. Reddy.
    SeriesNASA technical memorandum -- 103100.
    ContributionsReddy, T. S. R., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15296550M

      im working on simulation of a pipe flow with an orifice with supersonic flow with one end closed and the other end open. The flow near the inlet is patched to k and i am looking for the propogation of flame front to the open end. The fluid is taken as H2-O2 mixture at stiochiometric ratio, turbulence model as K-epsilon. Numerical Simulations of Supersonic Flow in a Linear Aerospike Micronozzle A Zilic University of Vermont D L. Hitt ‘boundary layers’ form on the expander wall section which can become sufficiently thick so as to retard the bulk Conservation of mass through the .

    Choked flow is a compressible flow effect. The parameter that becomes "choked" or "limited" is the fluid velocity. Choked flow is a fluid dynamic condition associated with the venturi a flowing fluid at a given pressure and temperature passes through a constriction (such as the throat of a convergent-divergent nozzle or a valve in a pipe) into a lower pressure environment the fluid. @article{osti_, title = {Numerical simulation on the dynamical stall process of airfoils in transonic flow}, author = {Guo, G L and Yang, Y N and Ye, Z Y}, abstractNote = {In this paper, a method is presented to simulate the dynamic stall process of airfoils in transonic flow. The flowfield around the oscillating airfoil is analyzed by solving the two-dimensional time averaged.

    in various cascade configurations in two-dimensional supersonic flow. This thesis was divided into three separate approaches to finding the shock angles: 1) analytical, 2) experimental, and 3) computational. The results from each section were compared using the analytical as a control. The analytical serves as the theoretical baseline. Background. Supersonic flow was a flow in which a Mach number is greater than , and this flow is very important in the design of aircraft and rockets. During the past, the experimental and analytical methods were used to simulate the properties of supersonic flow over a limited number of shapes, but for supersonic three-dimensional shapes such as a.


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Numerical simulations of supersonic flow through oscillating cascade sections Download PDF EPUB FB2

NUMERICAL SIMULATIONS OF SUPERSONIC FLOW THROUGH OSCILLATING CASCADE SECTIONS Dennis L. Huff National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio and T.S.R.

Reddy* The University of Toledo Toledo, Ohio Ahatta_. A finite difference code was developed for modeling inviscid, unsteady supersonic flow by solution of the compressible Euler equations. The code uses a deforming grid technique to capture the motion of the airfoils and can model oscillating cascades with any arbitrary interblade phase angle.

Get this from a library. Numerical simulations of supersonic flow through oscillating cascade sections. [Dennis L Huff; T S R Reddy; United States. National Aeronautics and Space Administration.].

The paper proposes a proper numerical approximation of boundary conditions suitable for cases with supersonic inlet and outlet flow velocities and compares the flow field for two cascade configurations: the first one corresponding to real experiment (cascade with finite number of blades located in the wind tunnel test section) and the second Author: J.

Fořt, J. Fürst, J. Halama, V. Hric, P. Louda, M. Luxa, D. Šimurda. The contribution deals with the numerical simulation of 2D compressible flow though the tip-section turbine blade cascade with the supersonic inlet boundary conditions.

Numerical investigation on the self-excited oscillation of wet steam flow in a supersonic turbine cascade Article in Progress in Natural Science 16(9) September with 48 Reads.

Numerical simulation of laminar viscous supersonic flow past a two-dimensional cavity Fluid Dynamics, Vol. 29, No. 6 Unsteady supersonic cavity flow simulations using coupled k-epsilon and Navier-Stokes equations. Transonic cascade wind tunnel.

An analysis target for this study is a transonic cascade wind tunnel in the University of Tokyo. This wind tunnel is designed for aeroelastic investigations of fan or compressor cascade, and it had been used for fundamental researches on the unsteady aerodynamic force characterist 17 and active suppression of cascade flutter Supersonic flow near an open rectangular cavity is numerically investigated in this work.

Such a flow is characterized by a complex unsteady flowfields. The computational region is presented on Figure geometrical parameters of cavity are: the ratio of the cavity length l to cavity depth h was l∕h = (l = mm, h = 3 mm).The inflow is parallel to the XY-plane and makes angle ψ. In this study, analysis of flow properties around a sphere and its aerodynamic coefficients in the high-Mach-and-low-Reynolds-numbers conditions is carried out by direct numerical simulations solving the three-dimensional compressible Navier–Stokes equations.

The calculation is performed on a boundary-fitted coordinate system with a high-order scheme of sufficient accuracy. The structure and oscillation characteristics of the shock train during steady and oscillatory flows in a supersonic cascade was experimentally studied.

The study was based on the SAV21 supersonic. Numerical Simulation of Oscillating Airfoil Unsteady Aerodynamics in Supersonic Flow Numerical Simulation of Oscillating Airfoil Unsteady Aerodynamics in Supersonic Flow Gallagher, Edward J.; Capece, Vincent R.

A contug problem the design turbomachery components for aircraft gas turbe enges is flow-duced vibrations. Numerical analysis of supersonic flow through oscillating cascade sections by using a deforming grid The reason for using the numerical Euler code over a small-perturbation theory is the ability to model real airfoils that have thickness and camber.

Sample predictions are presented for a section of the rotor on a supersonic throughflow. Computational study on flow through truncated conical plug nozzle with base bleed.

Propulsion and Power Research, Vol. 8, No. 2 Numerical simulations and physical analysis of an overexpanded reactive gas flow in a planar nozzle. Flow in a viscous jet escaping through a supersonic nozzle into a semi-infinite ambient space. Huff, D. L.; Reddy, T. R.; “Numerical Analysis of Supersonic Flow Through Oscillating Cascade Sections by Using a Deforming Grid”, AIAA paper 89–, AIAA/ASME/SAE/ASEE 25th Joint Propulsion Conference,Monterey, California, July 10–13, Google Scholar.

Get this from a library. Numerical analysis of supersonic flow through oscillating cascade sections by using a deforming grid. [Dennis L Huff; T S R Reddy; United. Numerical methods in MAC3 Numerical methods in the MAC3 group are used for simulations, to understand physical phenomena; used for simulations, to enhance analysis; and studied as mathematical objects (analysis of numerical methods): to understand the behaviour of methods, to design more efficient methods.

This talk is about the third item, the analysis of numerical. Numerical Analysis of Flow Through Oscillating Cascade Sections,”pp. – Lane. F.,“ Supersonic Flow Past on Oscillating Cascade With Supersonic Leading-Edge Locus,” J. Aero. Sci., Vol. 24 Numerical Simulations of the Aerodynamics of Horizontal Axis Wind Turbines.

A time-accurate Euler/Navier–Stokes analysis is applied to predict unsteady subsonic and transonic flows through a vibrating cascade. The intent is to validate this nonlinear analysis along with an existing linearized inviscid analysis via result comparisons for unsteady flows that are representative of those associated with blade flutter.

As one of supersonic mixing techniques, a supersonic mixing technique using a cavity and a porous wall has been proposed. The cavity and the porous wall generate the low speed region in the cavity, which enhances mixing the main flow with the jets. In this study, numerical simulations were conducted to clarify the effects of backward inclined jets on the mixing technique using a porous wall.

al. [16] conducted direct numerical simulations of the flow through regular porous media consisting of equally sized, staggered square cylinders. They found that the pressure drop dominates and the entrance and exit effects are negligible. Pamuk and Özdemir [17] stressed in their book section that it is.M.

Jithin, A. Mishra, A. De, M.K. Das. Numerical study of bifurcating flow through sudden expansions: effect of divergence and geometric asymmetry.

Int. Journal of Advances in Engineering Sciences and Applied Mathematics,8(4), P. Das, A. De. Numerical study of flow physics in supersonic base-flow with mass bleed.Physical Models. As can be seen in Fig. 1, Lx is the coordinate along the wall and its positive direction is from O to A to B to C.

Firstly, when width (L)-to-depth (D) ratio L/D = 1/6, numerical models under different conditions—attack angle (α) = 0°,15° and 30°—are performed separately to analyze the influence of attack angle on the flow around a gap.