Drag force investigation of cavities with different geometric configurations in supersonic flow

Luo, Shijun; Huang, Wei; Liu, Jun; Wang, Zhenguo

doi:10.1007/s11431-011-4320-5

Cited by 16 publications

(5 citation statements)

References 13 publications

(15 reference statements)

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“…Huang et al [14] have discussed numerically the effect of injection location on combustion performance of scramjets. Luo et al [15] showed that the rectangular cavity generates both the least additional drag force and the weakest combustion. Huang et al [2] numerically studied the L/D ratio and combustor back pressure for supersonic non-reacting flows.…”

Section: Introductionmentioning

confidence: 99%

Enhancing mixing features in supersonic flow through geometric correction of the cavity depth relative to the height of the combustion chamber

Abadi

Mirzabozorg

Kheradmand

2021

J Braz. Soc. Mech. Sci. Eng.

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The conventional method for cavity analysis is solving two-dimensional equations. The two-dimensional implicit and densitybased Reynolds averaged Navier-Stokes equations and the two-equation standard k-ε turbulence model have been employed to numerically simulate the cold flow field in a single-cavity flame-holding configuration of a supersonic combustor. The cross section of the combustor is assumed to be rectangular. The supersonic inlet is supposed for the steady and unsteady flow conditions along with normal directions to the inlet. For the validation purpose, the numerical results are compared with those of the experimental data available in the current literature. It is quite well-known that the cavity in supersonic combustors helps to separate the fuel from the wall configuration while improving the mixing process in supersonic flows. However, the selection of the most efficient depth for the cavity is crucial in obtaining optimum conditions. In the present research work, the role of the cavity length-to-height (L/D) ratio, the channel height-to-cavity height (H/D) ratio and Mach number are studied numerically. The obtained results indicate that the wall static pressure profiles of validation case predicted by the numerical approaches are well in agreement with those of the experimental data. Also, H/D = 2 was found to be the best choice for the combustion chamber height relative to the cavity depth. The designed geometry is modeled in a commercial software using two-dimensional density-based energy equations while the turbulent characteristics are modeled using standard k-ε turbulence model.

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Section: Introductionmentioning

confidence: 99%

Enhancing mixing features in supersonic flow through geometric correction of the cavity depth relative to the height of the combustion chamber

Abadi

Mirzabozorg

Kheradmand

2021

J Braz. Soc. Mech. Sci. Eng.

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“…[9] For this reason, the cavities with different configurations have been investigated numerically and experimentally by many researchers. [2,[10][11][12][13][14][15] Huang [2] investigated the influence of cavity configuration on the combustion flow field performance of the hypersonic vehicle, and found that the cavity with a sweptback angle of 45 ∘ could further improve the aero-propulsive performance of the hypersonic vehicle. He also investigated the influence of geometric parameters on the drag force of the heated flow field around the cavity by variance analysis method.…”

Section: Introductionmentioning

confidence: 99%

“…[10] The characteristics of the cavities with different shapes in the freestream with low velocity were experimentally tested by Ozalp. [11] Luo [12] estimated and compared the drag forces of three different geometric configurations of the cavity flame holder, namely the classical rectangular, triangular and semicircular, and the cavities were with the fixed depth and lengthto-depth ratio. He found that the triangular cavity imposes the most additional drag force on the scramjet engine, and the drag force of the classical rectangular one is the least.…”

Section: Introductionmentioning

confidence: 99%

Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method*

et al. 2021

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Near space has been paid more and more attentionin recent years due to its military application value. However, flow characteristics of some fundamental configurations (e.g., the cavity) in near space have rarely been investigated due to rarefied gas effects, which make the numerical simulation methods based on continuous flow hypothesis lose validity. In this work, the direct simulation Monte Carlo (DSMC), one of the most successful particle simulation methods in treating rarefied gas dynamics, is employed to explore flow characteristics of a hypersonic cavity with sweepback angle in near space by considering a variety of cases, such as the cavity at a wide range of altitudes 20–60 km, the cavity at freestream Mach numbers of 6–20, and the cavity with a sweepback angle of 30°–90°. By analyzing the simulation results, flow characteristics are obtained and meanwhile some interesting phenomena are also found. The primary recirculation region, which occupies the most area of the cavity, causes pressure and temperature stratification due to rotational motion of fluid inside it, whereas the pressure and temperature in the secondary recirculation region, which is a small vortex and locates at the lower left corner of the cavity, change slightly due to low-speed movement of fluid inside it. With the increase of altitude, both the primary and secondary recirculation regions contract greatly and it causes them to separate. A notable finding is that rotation direction of the secondary recirculation region would be reversed at a higher altitude. The overall effect of increasing the Mach number is that the velocity, pressure, and temperature within the cavity increase uniformly. The maximum pressure nearby the trailing edge of the cavity decreases rapidly as the sweepback angle increases, whereas the influence of sweepback angle on velocity distribution and maximum temperature within the cavity is slight.

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“…The flow fields, combustion characteristics, and performances of cavities with different configurations were widely researched in previous works. 6–13…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of combustion stabilization modes in a cavity-based supersonic combustor with different wall divergence angles

Zou

Liang

Sun

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Optical diagnostics and pressure measurements are carried out to investigate the characteristics of cavity-assisted hydrogen jet combustion in a Mach 2.52 supersonic flow which simulates flight Mach 5.5 ∼ 6 conditions. Two combustor configurations with wall divergence angles being 2.25° and 3.5°, and two injection schemes are designed. Main attention is focused on the influences of the combustor wall divergence angles and injection schemes on combustion stabilization modes. The experimental results show that two totally different combustion stabilization modes and transition processes between combustion stabilization modes are detected. Heat release and jet–cavity interactions are supposed to play an important role in the transition of combustion stabilization modes. In addition to injection schemes and the cavity configuration, the combustor wall divergence angle is demonstrated to obviously affect the combustion stabilization modes in the supersonic cavity flows, suggesting that the divergence angle should be seriously considered in the supersonic combustion organization. The contrastive experiments also show that as long as combined cavity shear layer/recirculation combustion stabilization mode is achieved, the divergence angle should be smaller and the injection distance should be shorter with all the possible means to obtain more stable combustion in present condition. Meanwhile, it needs to be more cautious to design injection schemes if the combustor wall divergence angle is larger.

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Drag force investigation of cavities with different geometric configurations in supersonic flow

Cited by 16 publications

References 13 publications

Enhancing mixing features in supersonic flow through geometric correction of the cavity depth relative to the height of the combustion chamber

Enhancing mixing features in supersonic flow through geometric correction of the cavity depth relative to the height of the combustion chamber

Investigation of hypersonic flows through a cavity with sweepback angle in near space using the DSMC method*

Experimental investigation of combustion stabilization modes in a cavity-based supersonic combustor with different wall divergence angles

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