Supersonic jet and crossflow interaction computational

Tests were conducted at Mach 4. The three remaining sides of the computational domain the exit plane, the top surface and the longitudinal plane opposite the symmetry plane do not represent any physical surface.

Study of parameters and entrainment of a jet in cross-flow arrangement with transition at two low Reynolds numbers.

The ideal-gas hot-air jet was found to represent the multispecies, hot-gas jet reasonably well, making it a viable substitution for a real-gas solution under certain assumptions.

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We conduct research into a variety of applications including: This indicates that the existence of the block has strengthened the coupling effect between the positive and negative vortex structures.

Flow control with noncircular jets. Supersonic jet and crossflow interaction computational simulations of a round jet in crossflow. In the real phenomenon the pressure recovery to the free stream occurs earlier than the CFD predicts.

A canonical geometry that can be used to study these interactions is an exisymmetric jet exhausted parallel to a compliant surface. However, an unwanted nose-down moment is also produced.

Fluids,18 2Roy, and Steven J. Large-eddy simulation of a round jet in a cross-flow. Full citation Abstract 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.

It is apparent that the block has a significant effect on the temperature field. Direct numerical simulation of round turbulent jets in crossflow.

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Also, the area used for the integration was 5. Large eddy simulation LES is not yet practical due to prohibitively large grid requirement near the wall. We are developing numerical methods, turbulence models and simulation tools that are flexible enough to handle multi-physics flows in engineering geometries without compromising the accuracy needed to simulate turbulence.

Large-eddy simulation of jet mixing in supersonic crossflows. For example, below are instantaneous stereo-PIV image of the velocity field at convective Mach numbers of 0.

The light source system consists of a 1. During the development, the CRVP remains a substantially symmetrical shape. The case of the main jet with the ramp shows a different shock shape from the main jet only case.

A unique 4 window test section design allows for adequate optical access for advanced flow diagnostic techniques to be employed, such as tomographic PIV. The CFD and PSP results are verified with pressure tap results, and all results are compared with the main jet only case and the ramp case.

The formations of three special shocks including a barrel shock, a bow shock, and a separation-induced shock wave were observed. In order to determine the flow field resulting from a single plasma actuator, micro-Particle Image Velocimetry was utilized to obtain the movie of the plasma actuator process.

Numerical Study of the Discrete Staggered Staged Sonic Jet Interaction in a Supersonic Crossflow. 21st AIAA International Space Planes and Hypersonics Technologies Conference.

Citation () Supersonic jet and crossflow interaction: Computational modeling. Progress in Aerospace Sciences 57, Online publication date: 1-Feb Aso et al.

() experimented on the influence of the jet-to-crossflow pressure ratio on the transverse injection flow field in supersonic flows, and found that the shapes of the bow shock wave, the Mach disk and the barrel shock wave are all enlarged with the increase of the jet-to-crossflow pressure ratio, and the separation point of the.

· reaction jet effects at supersonic speeds is the sonic injection of gaseous injectant through a nozzle and normal to a supersonic airstream over a flat plate.

The typical features of the interaction flowfield due to a transverse sonic jet in The lateral jet interaction on a slender body with rudders in supersonic flow had been investigated by numerical simulation, when the lateral jet is not in the longitudinal symmetry plane.

It was called Asymmetrical lateral jet interaction in this paper. The flow features of jet interaction flowfield on the surface of the body or in the space far from the surface at different angles of attack 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.

There is a general consensus on the qualitative structure of the flow at low speeds; however, the flow structure at low-velocity ratios (jet speed/crossflow speed) might be fundamentally different from the common notion of shear-layer vortices, counter-rotating vortex pairs, wakes, and horseshoe vortices.

Supersonic jet and crossflow interaction computational
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Asymmetrical Lateral Jet Interaction on a Slender Body in Supersonic Flow