Supersonic jet and crossflow interaction computational

Profiles of w have been inverted 10 in sign for the positive vortex. Out-of-plane velocity biases remain uncorrected primarily because this component of the error inexplicably varies with J and hence cannot be corrected using jet-off measurements.

The high pressure region of the PSP results is wider than the CFD result, and the separation shock region is also wider. While this creates a serious measurement bias near the jet exit due to selective flow sampling, data acquired further downstream are not subject to such a difficulty because turbulent mixing entrains particles from the freestream and spreads them throughout the interaction once in the far-field.

Similarly, the three turbulent shear stresses each exhibit distinctly different distributions. These results are shown in Fig. Utilizing a new supersonic missing layer tunnel the turbulence of the flow field has been measured using a variety of optical and laser based techniques to create a validation quality data set.

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At high velocity ratio, the RLV affected by the block in the JICF with block can still generate a stable performance near the nozzle, but the intensity is significantly decreasing. The precision 10 0. Prior to these tomographic PIV experiments, the existence of these complex vortical structures in this flow field could only be speculated.

Vijayaraja The acoustic and flow characteristics of a jet with elliptical throat is studied at different levels of nozzle expansion ratio. Note that according to the coordinate axis used to define the computational domain in this study, a negative pitching moment about the center of the primary jet indicates a nose-down moment.

Detailed flow physics of the supersonic jet interaction flow field.

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The upper Schlieren picture of Figure 11 is for the main jet only, and the lower picture is the main jet with ramp. B,88 4The crossplane PIV configuration aligns the freestream direction of the wind tunnel with the out-of- plane motion through the laser sheet; therefore, to limit the resulting particle dropout, the experiment used a thick laser sheet of 2.

In-plane velocities are displayed as vectors superposed upon a contour plot of the out-of-plane streamwise velocities. Department of Energy DOE. The ramp is also constructed from brass, and six pressure taps are on the ramp.

Aiming at the inadequacies of the existing liquid injection mechanism, a novel pulsed micro-injection technology based on an amplification piezoelectric actuator APA was presented. This threshold is somewhat J arbitrary in that it was selected not for any physical Fig.

Note that the final ramp design did not feature any plateau. This phenomenon indicates that the unstable performance of the JICF is closely related to the velocity ratio.

This should not be surprising, given that a Fig. The iterative convergence of the calculations was determined by checking the variation over time of several flow parameters.

Schematic of the camera arrangement for in Fig. The light source system consists of a 1.

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Air was injected through a circular injector into a Mach 4 crossflow with a pressure ratio ofand the 3D ramp was designed by parametric study using GASP.

A more extensive discussion of this phenomenon is found in Ref. Additionally, these results provide jet-in-crossflow data in the sparsely-studied transonic regime and are ideal for the validation of computational simulations and the evolution of their underlying physical models.

Table 1 shows the summary of the force and the moment coefficient results. Predictions of a sonic, multispecies, hot-gas jet using real-gas methodology are compared with predictions of a cold-gas jet and a hot, nonreacting jet using the ideal-gas assumption.

The inclined plane of the ramp shows a large region of high pressure. Therefore, the interaction between the reflected oblique shock and the fuel jet and the wall plays an important role of flame stabilization and enhancing combustion in supersonic transverse jet.

Flame structures on stream-wise (x/D) plane. · An estimate of the trajectory and strength of the CVP showed that there was little effect of the turbulence model on the location of the CVP but over a 30% difference in the maximum induced vorticity on the symmetry elleandrblog.com://elleandrblog.com  · As the incoming supersonic crossflow has a Mach number of aboutp jet /p ∞ =, i.e.

the static pressure of the jet outflow is only twice the free-stream pressure. Consequently, caused by the strong compression of the bow shock (pressure rise ratio above ), the local ambient pressure becomes larger than the jet elleandrblog.com  · 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.

Predictions of a sonic, multispecies, hot-gas jet using real-gas methodology are compared with predictions of a cold-gas jet and a hot, nonreacting jet using the ideal-gas elleandrblog.com://elleandrblog.com?id=  · Jet effluent chemistry models (chemical models which predict levels of ozone deple- tion) have traditionally ignored the observed entrainment of the hot exhaust products into the vortex wake system of the elleandrblog.com?.

Modelling of supersonic mixing and shock-wave structure in two jets interaction Mohammad Ali & Toshi Fujiwara Department of Aerospace Engineering, Nagoya University, NagoyaJapan a jet in crossflow encompassing the entire mixing region.

They confirmed the double vortex into the computational coordinate system .

Supersonic jet and crossflow interaction computational
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