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Sunday, October 4, 2020 | History

3 edition of Investigation of mixing a supersonic stream with the flow downstream of a wedge found in the catalog.

Investigation of mixing a supersonic stream with the flow downstream of a wedge

Investigation of mixing a supersonic stream with the flow downstream of a wedge

NCC2-5190 final report

  • 136 Want to read
  • 17 Currently reading

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

    Subjects:
  • Supersonic flow.,
  • Velocity distribution.,
  • Flow visualization.,
  • Flow distribution.,
  • Air flow.,
  • Gas injection.,
  • Mach number.,
  • Wind tunnel tests.,
  • Multiphase flow.

  • Edition Notes

    StatementJoseph Sheeley.
    Series[NASA contractor report] -- NASA-CR-204063., NASA contractor report -- NASA CR-204063.
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15538185M

      A detailed experimental investigation to understand and quantify the development of loss and blockage in the flow field of a transonic, axial flow compressor rotor has been undertaken. Detailed laser anemometer measurements were acquired upstream, within, and downstream of a transonic, axial compressor rotor operating at design and off-design.   A Mixing Theory for the Interaction Between Dissipative Flows and Nearly Isentropic Streams. Effect of Reynolds Number on Laminar Separation of a Supersonic Stream. Observations of turbulent reattachment behind an axisymmetric downstream-facing step in supersonic by:

    The flow on the fuel side of the mixing layer near the wedge base becomes subsonic because of the heat released by combustion. The higher pressure of the postshock gases around the impingement point is transmitted upstream along the subsonic fuel side, which contributes to the vase-like shape of Cited by: Chapter 6|Solution of Viscous-Flow Problems the velocities in order to obtain the velocity gradients; numerical predictions of process variables can also be made. Typesof° broad classes of viscous °ow will be illustrated in this chapter: 1. Poiseuille °ow, in which an applied pressure difierence causes °uid motion between File Size: KB.

    2. The Rappahannock River near Warrenton, VA, has a flow rate of m 3 s Tin Pot Run (a pristine stream) discharges into the Rappahannock at a flow rate of m 3 s To study mixing of the stream and river, a conservative tracer is added to Tin Pot Run. If the instruments that measure the tracer can detect a concentration of 1 File Size: 1MB. Axisymmetric flow and the flow downstream of separation. Journal of Fluid Mechanics , () The flow in the neighbourhood of the rim of a finite rotating by:


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Investigation of mixing a supersonic stream with the flow downstream of a wedge Download PDF EPUB FB2

Get this from a library. Investigation of mixing a supersonic stream with the flow downstream of a wedge: NCC final report. [Joseph Sheeley; United States. National Aeronautics and. SUPERSONIC FLOW ONTO A SOLID WEDGE K L I FIGURE Curve: downstream velocities for all possible shock nor-mals.

The left branch corresponds to compression shocks, the right branch to unphysical expansion shocks. The Cis exactly sonic, points left of it are subsonic, right of it Cited by: Supersonic Flow Over a Wedge Ahmed M Nagib Elmekawy, PhD, P.E. Problem Specification A uniform supersonic stream encounters a wedge with a half-angle of 15 degrees as shown in the figure below.

The stream is at the following conditions: We expect that the flow downstream of the shock will still be supersonic as theFile Size: 1MB. studied by many supersonic combustion researchers since ’s, but with limited free-stream °ow conditions.

Most of the previous research was performed in conventional wind tunnels by accelerating cold air into supersonic conditions, namely in low velocity and low total enthalpy °ow conditions. However, a real supersonic combustor environ.

Due to this volume increase of the stream tube the cone flow has two features/regimes which the wedge flow cannot have: The stream lines after the shock are curved (bent) so that they align with the cone geometry.

Certain flow-settings will result in a sonic-line within the flow downstream of the shock. But because the flow is non-isentropic, the total pressure downstream of the shock is always less than the total pressure upstream of the shock. There is a loss of total pressure associated with a shock wave.

On this page, we consider the supersonic flow of air past a two-dimensional wedge. The supersonic mixing layer flow, consisting of a relatively cold, slow diluted hydrogen stream and a hot, faster air stream, is numerically simulated with detailed transport properties and.

The numerical investigation of supersonic mixing of hydrogen with air has been performed in the work [5] [6]. For the process the main flow air entering through a finite width of inlet and gaseous.

Supersonic Wedge Flow: Study #2. Figure 1. The shading of the Mach number for the Mach flow past a 15 degree wedge with the creation of an oblique shock. Introduction. This study performs a grid convergence study of the WIND code for solving a simple supersonic flow past a wedge. Consider the supersonic flow of air at upstream conditions of 70 kPa and K and a Mach number of over a two-dimensional wedge of half-angle If the axis of the wedge is tilted with respect to the upstream air flow, determine the downstream Mach number, pressure, and temperature above the wedge.

Solution:File Size: KB. A Model for Characterization of a Vortex Pair Formed by Shock Passage Over a Light Gas Inhomogeneity Journal of Fluid Mechanics V ol.Januarypp. 33 Fuller, R. P., Wu, P. K., Nejad, A. S., and Schetz, J. A., Fu e l Vo r tex In teractions for enhanced Mixing in Supersonic Flow AIAA Paper 9632 nd AIAA/ASME/SAE/ASEE.

Some Exact Calculations Produced by a Wedge Either Directly or of the Lift and Drag in Supersonic Flow, by, Interference By P. ROE # Reports and Memoranda No.

* August, Summary. Exact inviscid theory is applied to a simple lifting configuration consisting of a wedge beneath a plane.

In well-known papers devoted to the investigation of supersonic streams adjacent to a wall, the authors, as a rule, restrict themselves to the case of a subsonic blast. In the present paper we determine the velocity field and the concentration field of an admixture of helium in a plane supersonic stream of air (M1=), propagating along a surface in an accompanying supersonic flow of air (M2 Cited by: 1.

Airflow stream and fuel stream has more interactions for wavy wall strut with additional shock waves and its reflections in-between combustion chamber walls and shear mixing layer. The intersection region between the supersonic flow and fuel stream is the shear mixing by: 2.

Abstract. The results are given of an experimental investigation of the flow in the initial section of a turbulent underexpanded jet exhausting from a profiled nozzle with Mach number M a = at the exit into a parallel stream with Mach number M ∞ = Analysis of the results of measurement of the fields of the total head p 0 and the stagnation temperature T 0 in conjunction with Author: I.

Karpman, V. Traskovskii. Inlet Flowfield Investigation Part II-Computation of the Flow About a Supercruise Forebody at Supersonic Speeds G. Paynter V. Salemann E. Strom Boeing Military Airplane Company Seattle,Washington Contract NAS April 0PY i,i.",",'?_it.q84 CENfEB RESEARC,4 LIBRARy, r,t,\SA NationalAeronauticsand HA.'./_TON,VIRGINIA.

An experimental investigation of the mixing of two coaxial gas streams was conducted over a range of subsonic jet Mach numbers and temperatures.

Three configurations were investigated. One had no innerbody in the primary or inner pipe and was designed to.

Report presents the results of experimental and theoretical research conducted on flow separation associated with steps, bases, compression corners, curved surfaces, shock-wave boundary-layer reflections, and configurations producing leading-edge separation.

Results were obtained from pressure-distribution measurements, shadowgraph observations, high-speed motion pictures, and oil Cited by: Physics Setup. Note that the look and arrangement of the menu setup in FLUENT has changed a bit since this tutorial was created.

If something has changed in the menu setup from the description below, you can often find the equivalent options by poking around in the menus. Mass flow is at a premium since all the propulsive mass is carried with vehicle, and very high exhaust speeds are desirable. B.E.

Milton and K Pianthong [2] work on. By symmetry, supersonic flow in a concave corner that turns though an angle is equivalent to one half of the flow pattern that results when a supersonic fluid is normally incident on a symmetric wedge of nose angle.

This is illustrated in Figure A mixing process may be described as follows: A stream with solute concentration C i (pounds/volume) is fed to a perfectly stirred tank at a constant flow rate of q (volume/time).

The perfectly mixed product is withdrawn from the tank, also at the flow rate q at the same concentration as the material in the tank C 0. The total volume of solution in the tank is constant at V. Density may be.Thus, in a converging supersonic flow, the pressure rises; in a diverging flow, it falls in the stream direction.

As a result, the pressure gradient at a convex corner is negative and the boundary layer generally negotiates the corner without separating, causing the effect of the boundary layer on the external or mainstream flow to be.