Numerical Simulations of a Cylinder-Induced Shock Wave/Boundary Layer Interaction

Lindörfer, Stefen A.; Combs, Christopher S.; Kreth, Phillip A.; Schmisseur, John D.

doi:10.2514/6.2017-0534

Cited by 10 publications

(4 citation statements)

References 25 publications

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“…An implicit density-based steady solver was chosen for the computations with Advection Upstream Splitting Method (AUSM) flux formulation. Previous studies (Cappelli & Mansour 2013;Lindörfer et al 2017) have reported that the 𝑘-𝜔 turbulence model over predicts the separation length in flows which involves strong SBLI, like in the present study. This over prediction of separation length was also observed in our earlier computations with 𝑘-𝜔 model.…”

Section: Computational Setupsupporting

confidence: 75%

On the scaling of three-dimensional shock-induced separated flow due to protuberances

2022

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Supersonic flow over 3-dimensional bodies protruding out of the turbulent boundary layer was investigated by means of experiments and numerical computations. A parametric study was performed by varying the shape and dimensions of the protuberance, as well as the freestream Mach number (1.5, 2, 2.5, 2.89, 3.5). The rise in surface pressure at mid-span due to separation (plateau pressure) was dependent only on the incoming flow parameters, and independent of protuberance geometry. The 2-dimensional free interaction theory closely predicts the mid-span plateau pressure. Although protuberances are of varying shapes and dimensions, the inviscid bow shock provided generalized scales. The radius of curvature of the inviscid shock on the wall plane at the nose, which is theoretically related to the local second derivative (along the shock) of pressure jump, was found to be a determining parameter of mid-span separation length (Lsep). Since the spanwise distance of the sonic point on the inviscid shock was found to be strongly correlated to its nose radius of curvature, it follows that the 'strong' portion of the inviscid bow shock fixes the mid-span separation location. These observations concerning mid-span plateau pressure, and the role of strong shock portion in fixing mid-span separation, suggest that the Lsep shall be predicted from a modification of the scaling laws for the length of plateau pressure region in 2-dimensional shock boundary layer interaction, with the inclusion of spanwise relieving effect. A correlation is obtained relating the Lsep with various incoming flow parameters and inviscid shock nose radius.

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Section: Computational Setupsupporting

confidence: 75%

On the scaling of three-dimensional shock-induced separated flow due to protuberances

2022

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“…An implicit density-based steady solver was chosen for the computations with Advection Upstream Splitting Method (AUSM) flux formulation. Previous studies (Cappelli & Mansour 2013;Lindörfer et al 2017) have reported that the -turbulence model over predicts the separation length in flows which involves strong SBLI, like in the present study. This over prediction of separation length was also observed in our earlier computations with -model.…”

Section: Computational Setupsupporting

confidence: 74%

Three dimensional shock induced separated flow

Bhardwaj¹,

Rengaran²,

Vamsi³

2021

Preprint

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Supersonic flow over 3-dimensional bodies protruding out of the turbulent boundary layer was investigated by performing experiments and numerical computations. A parametric study was undertaken varying shapes, heights, and diameters of the protuberance. To study the Mach number effects on the shock boundary layer interactions due to protuberances flows with varying Mach numbers (1.5, 2, 2.5, 3, 3.5) were also examined. Surface oil flow technique, surface pressure measurements and schlieren flow visualization using a high-speed camera were employed along with 3-dimensional RANS computations to elicit flow features such as core of the horseshoe vortex, which greatly influences the flow in recirculation bubble. Though some of the parameters involved in such interactions are individually investigated in the literature, a comprehensive study is still lacking. It was observed that the viscous interaction was strongly related to the inviscid phenomenon happening close to the surface of the protuberance. Radius of curvature of the inviscid shock at the nose was found to be a determining parameter incorporating information on adverse pressure gradient experienced by local boundary layer, geometrical parameters of the protuberances, and Mach number of the incoming flow. Based on this, a scaling law is presented to relate the separation length involved in such interaction with various geometrical and incoming flow parameters. The scaled separation length was predicted remarkably well by the proposed correlation. As a comprehensive correlation, it was also tested with data from a 2-dimensional forward facing step study in the literature, and a good agreement was found. It was also observed that the location of the horseshoe vortex core was also dependent on the inviscid shock in the same way as is separation length.

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“…Проведенные расчеты для различных наборов определяющих параметров показывают, что общая картина течения в области соединения тела и пластины получается схожей по структуре для всех вариантов: наблюдается обширная отрывная область перед телом, головной скачок уплотнения, а также косые волны уплотнения, формирующиеся при обтекании отрывной области. Аналогично работе [14] данная общая структура течения в плоскости симметрии может быть изображена схематично в виде, представленном на рис. 5.…”

Section: изменения в структуре потока при варьировании параметров задачиunclassified

“…Недавние публикации [8][9][10][11][12][13][14][15] показывают, что интерес к данной тематике возрос с выраженным уклоном в сторону проведения расчетных работ [8][9][10][11][12][13][14]. Исследования проводятся как для ламинарных режимов течения [9][10][11][12][13], так и турбулентных режимов [8,14,15], в последнем случае обычно решаются осредненные по Рейнольдсу уравнения Навье-Стокса (RANS подход) [14], однако имеются и попытки применения метода моделирования крупных вихрей (метод LES) для расчета течений данного класса [8].…”

Section: Introductionunclassified

Численное Исследование Вихревых Структур И Теплообмена При Сверхзвуковом Обтекании Области Сопряжения Затупленного Тела И Пластины

Колесник¹,

Смирнов²

2020

Журнал Технической Физики

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In the paper, the results of numerical simulation of a supersonic laminar flow past a fin-body junction are presented. The gas-dynamic and vortex structure of the flow, determined by viscous-inviscid interaction, is analyzed. Numerical data showing the qualitative and quantitative effects on the flow structure and heat transfer of the following parameters: Mach number, Reynolds number, temperature factor and plate length, are presented

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Numerical Simulations of a Cylinder-Induced Shock Wave/Boundary Layer Interaction

Cited by 10 publications

References 25 publications

On the scaling of three-dimensional shock-induced separated flow due to protuberances

On the scaling of three-dimensional shock-induced separated flow due to protuberances

Three dimensional shock induced separated flow

Численное Исследование Вихревых Структур И Теплообмена При Сверхзвуковом Обтекании Области Сопряжения Затупленного Тела И Пластины

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