An evaluation of nozzle relaminarization using Low Reynolds Number k-epsilon turbulence models

Jentink, Thomas N.

doi:10.2514/6.1993-610

Cited by 5 publications

(1 citation statement)

References 8 publications

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“…Hence, measurements for an instrument validation study need to be made as close as possible to the nozzle exit, typically less than a radius away from the nozzle. 17 have show a tur e transition and revert to a laminar-like behavior nt and cooling for our nozzle) is rem reement with the measured values for all the f a standard deviation of 0.04 atm, equal to or larger than the difference between the measured and computed pressure.…”

Section: A Numerical Resultsmentioning

confidence: 89%

An Experimental and Numerical Study of a Supersonic Burner for CFD Model Development

Magnotti¹,

Cutler²

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A laboratory scale supersonic burner has been developed for validation of computational fluid dynamics models. Detailed numerical simulations were performed for the flow inside the combustor, and coupled with finite element thermal analysis to obtain more accurate outflow conditions. A database of nozzle exit profiles for a wide range of conditions of interest was generated to be used as boundary conditions for simulation of the external jet, or for validation of non-intrusive measurement techniques. A set of experiments was performed to validate the numerical results. In particular, temperature measurements obtained by using an infrared camera show that the computed heat transfer was larger than the measured value. Relaminarization in the convergent part of the nozzle was found to be responsible for this discrepancy, and further numerical simulations sustained this conclusion.

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Section: A Numerical Resultsmentioning

confidence: 89%

An Experimental and Numerical Study of a Supersonic Burner for CFD Model Development

Magnotti¹,

Cutler²

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Scramjet Nozzle/Aftbody

2022

Scramjet Propulsion

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Influence of the Development History of Nozzle Wall Boundary Layer upon Wave Generation on a Liquid Jet Free Surface

Itoh

Kumamaru

2009

JFST

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The relation between the development of the wall boundary layer in a convergent nozzle and free surface waves on the emanated liquid jet has been investigated experimentally. In the convergent nozzle, which forms a water jet along a flat back wall, the velocity profiles of the wall boundary layer were measured using a laser Doppler velocimeter with jet average velocities of U 0 = 5, 10 and 15 m/s. The property of free-surface waves and the intermittency factor of free surface fluctuations were also determined by photography and an optical measurement technique, using laser beam refraction on the jet surface. For the lowest velocity case U 0 = 5 m/s, the mean velocity profiles of the boundary layer under the pressure gradient in the convergent nozzle indicated an inverse transition from turbulent to laminar boundary layer, so-called relaminarization. On the other hand, for the higher velocity case U 0 ≥ 10 m/s, the relaminarization in the convergent section became incomplete. For these cases, the turbulent intensity near the wall increased significantly and the nozzle-exit boundary layer was restored quickly to a turbulent profile for a short parallel section immediately upstream of the nozzle exit plane. The increase in the velocity fluctuation near the wall promotes wave generation downstream of the nozzle exit plane. Therefore, the intermittence of the wave packet almost disappeared and the jet free surface was covered with continuous capillary waves when the turbulent boundary layer was separated from the nozzle exit.

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An evaluation of nozzle relaminarization using Low Reynolds Number k-epsilon turbulence models

Cited by 5 publications

References 8 publications

An Experimental and Numerical Study of a Supersonic Burner for CFD Model Development

An Experimental and Numerical Study of a Supersonic Burner for CFD Model Development

Scramjet Nozzle/Aftbody

Influence of the Development History of Nozzle Wall Boundary Layer upon Wave Generation on a Liquid Jet Free Surface

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