Interaction of a side jet with a supersonic main stream

Interaction of a side jet with a supersonic main stream by Mark Vladimir Morkovin Download PDF EPUB FB2

Get this from a library. Interaction of a side jet with a supersonic main stream. [Mark Vladimir Morkovin]. Interaction of a supersonic stream and a transverse supersonic jet. Two-dimensional jet interaction flowfield predictions with an algebraic turbulence model.

Analysis of the flow-disturbance and side forces due to gaseous secondary injection into a rocket by: Vinson, P.W., J.L. Amick, and H.P. Liepmann: Interaction Effects Produced by Jet Exhausting Laterally Near Base of Ogive–Cylinder Model in Supersonic Main Stream, NASA Memo 12–5–58W, February Google ScholarAuthor: Andrew F.

Charwat. Two-dimensional secondary jet interaction with a supersonic stream. Two-dimensional jet interaction studies at large values of Reynolds and Mach numbers. Frank W. Spaid ; 17 May | AIAA Journal, Vol. 13, No. Experiments on the propagation of mixing and combustion injecting hydrogen transversely into hot supersonic by: The experimentally determined interaction effects of a side jet exhausting near the base of an ogive-cylinder model are presented and discussed.

The interaction force appears to be independent of main-stream Mach number, boundary-layer condition (laminar Author: J. Amick, P. Vinson and H. Liepman. The supersonic jet interaction flow field generated by a sonic circular jet with a pressure ratio of exhausting into a turbulent MACH cross flow over a flat plate was investigated using numerical simulations.

The simulations made use of the three-dimensional Reynolds-averaged Navier–Stokes (RANS) equations coupled with Wilcox’s k-ω turbulence model. Several control jets (CJ) can be used in order to improve the mixing in the initial part of a supersonic jet. This kind of device has been proved to be efficient in subsonic flows.

Supersonic fluid flow and the interaction of strong shock waves to produce jets of material are ubiquitous features of inertial confinement fusion (ICF), astrophysics, and other fields of high energy-density science.

The availability of large laser systems provides an opportunity to investigate such hydrodynamic systems in the laboratory, and to test their modeling by radiation hydrocodes.

Aerospace Science and Technology Interaction Between a Supersonic Hot Jet and a Coaxial Supersonic Flow/ Interaction entre un jet chaud supersonique et un oulement supersonique coaxial [6] Addy A. - Effects of Axisymmetric Sonic Nozzle Geometry on Mach Disc Characteristics, AIAA J., 19, January [7] Clemens N.

T., Mungal M. Transverse injection from a wall orifice is one of the simplest and most promising configurations to enhance the mixing process between the fuel and air in supersonic flows, and it attracts an increasing attention since the early sixties, especially on some scramjet powered vehicles, see Fig.

Fig. 1 represents the computational results obtained by the large eddy simulation. A transverse jet in the supersonic crossflow is one of the most promising injection schemes in scramjet, where the control or enhancement of jet mixing is a critical issue.

In this paper, the effect of the backward facing step on the characteristics of jet mixing was investigated by three-dimensional large eddy simulation (LES). The simulation in the flat plate configuration (step height of 0.

As the liquid jet is injected to a supersonic crossflow from a circular hole, a great number of small droplets with D interaction in the near-nozzle region compared with other regions, which is reflected in the greater proportion of small droplets with D.

First, the use of a "solid body" drag model to describe the jet trajectory is re-examined, extended to include a supersonic main stream, and modified to alleviate the most untenable of the.

Both primary and secondary fluids were air at the same stagnation temperature, but the secondary stagnation pressure was varied from about to 2 times the primary value; injection was sonic and the jet issued into the primary stream through a slit of constant width at 0 deg, 8 deg, 23 deg, and 50 deg upstream (the angle being measured from.

A group of scientists at NASA‘s Ames Research Center in Mountain View, Calif. has successfully captured the first images showing interactions of supersonic jet shockwaves. The technique used to record them has been in development for over 10 years.

NASA says this breakthrough will greatly contribute to its Aeronautics Research Mission Directorate. Jet streams are fast flowing, narrow, meandering air currents in the atmospheres of some planets, including Earth. On Earth, the main jet streams are located near the altitude of the tropopause and are westerly winds (flowing west to east).

Their paths typically have a meandering shape. Jet streams may start, stop, split into two or more parts, combine into one stream, or flow in various. Interaction between a supersonic airstream and a sonic jet injected through a diamond-shaped orifice. Mixing of a Hydrogen Jet from a Wedge Shaped Injector into a Supersonic Cross Flow.

Optimization of the Fuel Injector for the Supersonic Combustor Using a. Why can't jet engines operate with supersonic air. "Because there has been no business case to develop an engine with supersonic flow at entry to the compressor." The advantages would be the same that led to todays transonic (supersonic relative flow over part of the blade span) compressors, ie smaller and lighter.

A rocket engine uses a nozzle to accelerate hot exhaust to produce thrust as described by Newton's third law of motion. The amount of thrust produced by the engine depends on the mass flow rate through the engine, the exit velocity of the flow, and the pressure at the exit of the engine.

The value of these three flow variables are all determined by the rocket nozzle design. It centers on supersonic jets that can fly faster than the speed of sound, or miles per hour.

Indeed, while most commercial airliners today fly at between and miles per hour [ ]. Brown, A. M.,“Characterization of Side Load Phenomena Using Measurement of Fluid/Structure Interaction,” 38th Joint Propulsion Conference and Exhibit, AIAA Paper No.

Pekkari, L.-O.,“Aeroelastic Stability of Supersonic Nozzles With Separated Flow,” 29th Joint Propulsion Conference and Exhibit, AIAA Paper No. Dubbed the AS2, the supersonic private jet would comfortably fit 12 passengers while achieving a cruising speed of Mach by way of its three .Supersonic Flow Jet x y z Figure 1: Schematic representation of the general flow field developing due to the side jet interaction.

If KF exceeds 1, there is a gain additionally to the thrust of the jet itself resulting from the interaction of the side jet with the flow, if it is smaller than 1, the jet thrust is alleviated.