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2 edition of Velocity gradient method for calculating velocities in an axisymmetric annular duct found in the catalog.

Velocity gradient method for calculating velocities in an axisymmetric annular duct

Theodore Katsanis

Velocity gradient method for calculating velocities in an axisymmetric annular duct

by Theodore Katsanis

  • 36 Want to read
  • 38 Currently reading

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

    Subjects:
  • Air ducts,
  • Flow meters,
  • Unsteady flow (Aerodynamics)

  • Edition Notes

    StatementTheodore Katsanis
    SeriesNASA technical paper -- 2029
    ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
    The Physical Object
    Pagination20 p. :
    Number of Pages20
    ID Numbers
    Open LibraryOL14933163M

    pressures at those two locations. The pressure gradient may be caused by a pump and/or gravity. Note that we adopt a modified cylindrical coordinate system here with x instead of z for the axial component, namely, ()rx,,θ and ()uu ur,,θ. Derive an expression for the velocity field in the annular space in the pipe. Axisymmetric fluid flow. Ask Question Asked 6 years, 2 months ago. Fluid-solid coupling, how to impose both normal stress and velocity? 2. Governing equations and boundary conditions for a steady-state compressible viscous flow in an axisymmetric annular orifice. 1.

    MEASUREMENTS OF FLOWS OVER AN AXISYMMETRIC BODY WITH VARIOUS APPENDAGES IN A WIND TUNNEL: THE DARPA SUBOFF EXPERIMENTAL PROGRAM. Pressures, velocities, skin friction, and Reynolds stresses were measured in the stern boundary layer region of an axisymmetric body with and without maisonneuve-group.com by: 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.

    Use of arbitrary quasi-orthogonals for calculating flow distribution in the meridional plane of a turbomachine. NASA TN D Katsanis, T. and McNally, W.D. (). Revised Fortran program for calculating velocities and streamlines on the hub-shroud midchannel stream surface of an axial-, radial-, or mixed-flow turbomachine or annular duct. Show that the velocity potential Φ(r, z) in axisymmetric cylindrical coordinates (see Fig. ) is defined such that. Further show that for incompressible flow this potential satisfies Laplace’s equation in (r, z) maisonneuve-group.comnce Fig. %(4).


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Velocity gradient method for calculating velocities in an axisymmetric annular duct by Theodore Katsanis Download PDF EPUB FB2

Get this from a library. Velocity gradient method for calculating velocities in an axisymmetric annular duct. [Theodore Katsanis; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.]. Jul 09,  · Velocity gradient method for calculating velocities in an asymmetric annular duct.

Turbomachinery components are often connected by ducts, which are usually annular. The configurations and aerodynamic characteristics of these ducts are crucial to the optimum performance of the turbomachinery blade rows.

Apr 07,  · Velocity gradient expression in 2D-axisymmetric. Posted Apr 28,AM PDT Fluid, Computational Fluid Dynamics (CFD), Modeling Tools, Parameters, Variables, & Functions Version a, Version a 10 Replies.

Velocity gradient method for calculating velocities in an axisymmetric annular duct / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and. When the fluid velocity is written in this form it becomes obvious that the incompressibility constraint is satisfied [because --see Equations and ()].It is also clear that the Stokes stream function, is undefined to an arbitrary additive constant.

In fact, the most general. Non-Axisymmetric Line Driven Disc Winds II - Full Velocity Gradient 3 of the CAK formulation where the radiation force due to lines is Frad L = " M(t) n ˙ eId c ; (8) and M(t) is the so-called force multiplier.

The force mul-tiplier parametrizes how many lines are e ectively avail-able to increase the scattering coe cient. We use the OCR. Non-axisymmetric instability of core-annular fro w volume flux of each fluid in the linear theory of stability. Denote the viscosity and the density for the fluid 1 and fluid 2 as (p1, pl) and (p2, p2), respectively.

The radius of the pipe is R. We scale the length with the mean radius of the core R, the velocity with the centre. The technique described is capable of tackling the so-called inverse problem where the velocity wall distributions are prescribed from which the duct wall shape is calculated, as well as the direct problem where the velocity distribution on the duct walls are calculated from prescribed duct wall maisonneuve-group.com: Vasos Pavlika.

A method was designed for determining the shape of an axisymmetric body from a given velocity distribution in its meridional cross section. The method is based on an iterative process involving. Viscous flow in pipe Henryk Kudela Contents 1 Laminar or turbulent flow 1 2 Balance of Momentum - Navier-Stokes Equation 2 An understanding of the method of analysis and the results obtained Since the flow is axisymmetric about the centerline, the velocity is constant on small area.

In nonideal fluid dynamics, the Hagen–Poiseuille equation, also known as the Hagen–Poiseuille law, Poiseuille law or Poiseuille equation, is a physical law that gives the pressure drop in an incompressible and Newtonian fluid in laminar flow flowing through a long cylindrical pipe of constant cross section.

It can be successfully applied to air flow in lung alveoli, or the flow through a. Aug 29,  · Hey there, your BCs look just fine, just be care of setting the boundary conditions. On a staggered grid setting u = 0 (wall condition in the y-direction) is done as setting u(bc) = -u(end) so your boundary condition will the -1*the value of u close to the wall, due to.

In the present work, a Lattice Boltzmann formulation in vorticity-stream function variables is proposed for axisymmetric flows with swirl. For this purpose, several source terms are proposed and implemented. Although containing velocity gradients, these sources are in the Lattice Boltzmann framework and fulfill the Euler and Navier-Stokes equations in their conservative maisonneuve-group.com: Omar D.

Lopez, Sergio Pedraza, Jose R. Toro. NUMERICAL COMPUTATION OF SHOCK WAVE - TURBULENT BOUNDARY LAYER INTERACTION IN TRANSONIC FLOW OVER AN AXISYMMETRIC CUKVED HILL S.-W. Kimgr Institute for Computational Mechanics in Propulsion Lewis Research Center Cleveland, Ohio Summary A control-volume based finite difference computation of a turbulent.

A Boundary element method for calculating the shape and velocity of two-dimensional long bubble in stagnant and flowing liquid of the velocity gradient there), the free surface profile is. Example 1 A variable mesh screen produces a linear and axisymmetric velocity profile.

in the air flow through a 2 ft diameter circular cross-section duct as shown below. The static pressures upstream and downstream of the screen are psi and psi and are. uniformly distributed over the flow cross sectional area. Neglect friction exerted by the.

The evaluation of the axial velocity profile in the region before the outflow from the burner slots (Fig. 5) is quite similar for the two flame maisonneuve-group.com radial coordinate in the graph is normalised to the cylinder duct radius. The velocity is different from zero (order of magnitude of cm/s: this value is in agreement with that one evaluated from the relation total mass flow rate/cylinder.

An unsteady transient axisymmetric turbulent jet was studied experimentally. The initial flow perturbation consisted of a sudden and large decrease in the ejection velocity.

The temporal evolution of the mean and fluctuating unsteady velocity field was measured by using X hot-wire probes. In the jet far field, adaptation of the externally imposed unsteadiness to the local jet time scale is Cited by: axisymmetric, inviscid, incompressible, rotational (and irrotational) flow in order to obtain duct wall shapes from prescribed wall velocity distributions.

The governing equations are formulated in terms of the stream function x y (,) and the function x y (,) as independent variables where for. A first-order ordinary differential equation is obtained to study the motion of the trajectory of motion of a material particle in a two-dimensional (axisymmetric) conservative field.

The advantages of using the proposed equation in the numerical analysis of electron-optical systems are maisonneuve-group.com: A.A. Trubitsyn. Method (FEM) of Eversman, etc.5 as well as the multiple-scales (MS) method of Rienstra.6 In this paper, a D CAA approach is given, which is numerically based on our previous 2D CAA procedure.7 This procedure is firstly validated in comparison with the analytical solutions in .axisymmetric, inviscid, compressible and rotational and irrotational flow.

The algorithm is capable of calculating the duct wall geometries from prescribed wall velocity distributions. The equations modeling the flow are expressed using the stream function (x, y) and the function (x, y) as independent.Behaviour of Mean Velocity in the Turbulent Axisymmetric Outer Near Wake difference method on equations of motion with an appropriate eddy viscosity assumption.

Cebeci () further made an analysis on the deviation of the cylinder skin friction from that of a flat maisonneuve-group.com by: 1.