Boundary layer suction for high-speed air intakes: A review

Sepahi-Younsi, Javad; Feshalami, Behzad Forouzi; Maadi, Seyed Reza; Soltani, Mohammad Reza

doi:10.1177/0954410018793262

Cited by 29 publications

(8 citation statements)

References 80 publications

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“…In order to prevent separation and suppress buzz oscillations, many methods of flow control are examined in various literature, such as boundary layer suction [29], bleeding and injection [30], and vortex generators [31]. Some new techniques, for example micro-vortex generator [32], plasma actuators [33], and cavity [34] are also verified to be effective.…”

Section: Excitation Results Of Nonlinear Simulationmentioning

confidence: 99%

Acoustic Modeling and Vibration Characteristics of Supersonic Inlet Buzz

et al. 2020

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The buzz phenomenon of a typical supersonic inlet is analyzed on the basis of numerical simulations and duct acoustic theory. Considering that the choked inlet could be treated as a duct with one end closed, a one-dimensional (1D) mathematical model based on the duct acoustic theory is proposed to describe the periodic pressure oscillation of the little buzz and the big buzz. The results of the acoustic model agree well with that of the numerical simulations and the experimental data. It could verify that the dominated oscillation patterns of the little buzz and the big buzz are closely related to the first and second resonant mode of the standing wave, respectively. The discrepancies between the numerical simulation and the ideal acoustic model might be attributed to the viscous damping in the fluid oscillation system. In order to explore the damping, a small perturbation jet is introduced to trigger the resonance of the buzz system and the nonlinear amplification effect of resonance might be helpful to estimate the damping. Through the comparison between the linear acoustic model and the nonlinear simulation, the calculated pressure oscillation damping of the little buzz and the big buzz are 0.33 and 0.16, which could be regarded as an estimation of real damping.

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Section: Excitation Results Of Nonlinear Simulationmentioning

confidence: 99%

Acoustic Modeling and Vibration Characteristics of Supersonic Inlet Buzz

et al. 2020

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“…( 14) is that it depends solely on the geometric area of the bleed hole, not the particulars of the length, width, or angle, which makes Q model in Eq. (15) to depend solely on the incoming Mach number and the bleed chamber pressure ratio. The intrinsic physical reasoning is that the disturbance is limited within the Mach cone for supersonic flow.…”

Section: A Supersonic Inviscid Bleed Modelmentioning

confidence: 99%

“…Most modern bleed devices installed in air inlets use a porous array bleed system [15,16] because these can obtain a relatively uniform flowfield to reduce the total pressure loss and friction [17]. However, in the pursuit of a more universal bleed model, the present study extracts a single-hole bleed problem from a complicated bleed device, eliminating the mutual interactions among the bleed holes.…”

mentioning

confidence: 99%

Supersonic Bleed Rate Model for a Circular Orifice Based on Geometric Similarity

et al. 2020

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On the basis of the geometric similarity between polygons and circles, a bleed rate model of a supersonic inviscid circular hole is first established through a gradual approximation by regular polygons. The bleed mass-flow rate depends on the parameters at the entrance. A supersonic inviscid bleed choking model is further established by using the inflow Mach number and the pressure ratio when the expansion wave is parallel to the entrance. For a depthless hole at Mach 2.0 and with a pressure ratio of 0.5, the difference of flow coefficient predicted by the present model to that of computational fluid dynamics is 1.4% under nonchoking conditions. Under choking conditions with a pressure ratio of 0.1, the difference is 3.1%. Furthermore, the influence of the boundary layer on the bleed mass-flow rate is transformed into the influence of the displacement thickness on the effective size of the bleed hole. Based on that, the viscous bleed rate model is established, which shows a maximum error of 7.7% for a depthless bleed hole over laminar flow at Mach 4.0 and Reynolds number 2.590 × 10 5 . Compared with the reported results of the full bleed hole, the difference of the bleed mass-flow rate predicted by the present model is 3.8%.

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“…The performance of a hypersonic inlet bleed system depends on many factors, including the position, angle, and shape of the bleed hole. Martin et al (2007) by computational fluid dynamics (CFD) showed that total pressure recovery increased by 2% by 1% bleed mass flow rate, 1% by 2% bleed mass flow rate, and almost the same by 4% bleed mass flow rate, indicating the existence of the best appropriate bleed mass flow rate. Syberg and Hickcox (1973) studied the influence of the inclination angle of the bleed hole, the distance between the holes, and the diameter of the hole on the bleed mass flow rate.…”

Section: Introductionmentioning

confidence: 99%

Effects of bleed hole size on supersonic boundary layer bleed mass flow rate

Zhang

Zhao

Liu

2020

J. Zhejiang Univ. Sci. A

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The bleed hole diameter, depth, and boundary layer thickness are key design parameters of a supersonic bleed system. The evolution trend of single-hole bleed flow coefficient with the ratio of boundary layer thickness to bleed hole diameter and the ratio of bleed hole depth to diameter is investigated by numerical simulations under choking and non-choking conditions. The results show that the subsonic leading edge of the circular hole and the subsonic part of the boundary layer are the main factors causing lateral flow of the bleed hole. The effect of diameter on bleed mass flow rate is due to the viscous effect which reduces the effective diameter. The larger the ratio of displacement thickness to bleed hole diameter, the more obvious the viscous effect is. The depth affects bleed flow rate by changing the opening and closing states of the separation zone. When a certain depth is reached, the development of the boundary layer reduces the effective captured stream tube and thus reduces the bleed mass flow rate. The main objective of the study is to obtain the physical mechanism of the bleed hole size parameters affecting the bleed mass flow rate, and to provide theoretical guidance for the selection of the size of bleed holes in the design of a porous arrays bleed system in hypersonic inlets.

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Boundary layer suction for high-speed air intakes: A review

Cited by 29 publications

References 80 publications

Acoustic Modeling and Vibration Characteristics of Supersonic Inlet Buzz

Acoustic Modeling and Vibration Characteristics of Supersonic Inlet Buzz

Supersonic Bleed Rate Model for a Circular Orifice Based on Geometric Similarity

Effects of bleed hole size on supersonic boundary layer bleed mass flow rate

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