Supersonic jet and crossflow interaction computational

Direct numerical simulation of round turbulent jets in crossflow. Mechanisms for microparticle dispersion in a jet in crossflow. Because of its important engineering application and theoretical value, JICF has drawn attention of many researchers [ 3 Kawai, S.

Supersonic jet and crossflow interaction computational

Vijayaraja The acoustic and flow characteristics of a jet with elliptical throat is studied at different levels of nozzle expansion ratio.


In this study, we have taken two types of CD nozzle configuration circular and elliptical throat and it is studied for various NPR ratios of 2, 3, 4 and 6. In addition, the acoustic characteristic of the jet flow is also measured for respective NPRs.

Measurements of acoustic data are done using microphones placed at 30, 60 and 90 degrees to imprison the effects of screech tone.

Gas Dynamics Laboratory | Aerospace at Illinois The goal was to reduce the low pressure region behind the jet which produces an unwanted nose-down moment on a vehicle.
Jet in cross-flow experiment July ; 60 pages Abstract: Computational fluid dynamic predictions of surface pressures resulting from lateral jet injection into a Mach 3 supersonic crossflow from a cone-cylinder-flare missile are compared with wind tunnel data.
Personal Information Plasma generation, by means of AC or DV electrical discharges or optical laser breakdown, is used to control the flowfield of simple atmospheric flames, subsonic and supersonic boundary layers, and supersonic base flows. These effects are probed by a variety of optical diagnostics in order to measure velocity, temperature, and species concentrations in order to develop an understanding of the benefits of plasma actuators in these types of flows.
Mahesh group: Homepage All wind tunnels are blowdown type, with wind speeds ranging from subsonic to Mach 4. A few wind tunnels are of a more general design and can be used for the study of numerous flow fields while others are more specialized for the study of specific flows including axisymmetric and planar base flows, planar mixing layers, and transverse jet injection into supersonic crossflow.
Supersonic jet and crossflow interaction: Computational modeling - ScienceDirect Login LES of an inclined sonic jet into a turbulent crossflow at Mach 3.

At NPR 2, 3 and 4, the jet with elliptical throat witnesses superior mixing and shorter core length compared to the circular throat. Its surprising to see both the configurations provides the identical oscillation at NPR 2, 3 and 4, however the efficiency of jet mixing is larger in elliptical throat jet.

Supersonic jet and crossflow interaction computational

At NPR 2 and 3, the centerline pitot pressure profile shows, the decay of jet from the elliptical throat is healthier than a circular jet.

At various levels of nozzle expansion, shock cell shows an appreciable change with an increase in NPR.

Applications of Structured Meshing

Introduction of the elliptical throat on circular modifies the structure of shock cell which significantly changes the magnitude of screech tone due to the weakening of shock waves.Jet in crossflow mixing 1.

Effect of Jet Configuration on Transverse Jet Mixing Process Sin Hyen Kim, Yonduck Sung, Venkat Raman Department of Aerospace Engineering and Engineering Mechanics The University of Texas at A particle image velocimetry instrument has been constructed for a transonic wind tunnel and applied to study the interaction created by a supersonic axisymmetric jet exhausting from a flat plate into a subsonic compressible crossflow.

· counter-rotating vortex pair produced by the jet-in-crossflow interaction. There has been extensive research completed on the complexities of the flow field surrounding a jet in supersonic crossflow on a finned The supersonic jet-in-crossflow problem which involves shocks, turbulent mixing, and large-scale vortical structures, requires special treatment for turbulence to obtain accurate solutions.

Different turbulence modeling techniques are reviewed and compared in terms of their performance in predicting results consistent with the experimental data.

Flow Characteristics of a Low Reynolds Number Jet in Crossflow with an Obstacle Block

1 American Institute of Aeronautics and Astronautics An Analytical Approach to Modeling Supersonic Retropropulsion Flow Field Components Christopher E. Cordell, Jr.1, and Robert D. Braun2 Georgia Institute of Technology, Atlanta, GA, An unconfined overpressured jet contains a supersonic core bounded by barrel shocks, a normal shock referred to as a Mach disk shock, and oblique shocks (Figure

Combustion, Flow, and Plasma Interaction Laboratory | Aerospace at Illinois