Modeling of Fixed-Exit Porous Bleed Systems for Supersonic Inlets

Slater, John W.; Saunders, John D.

doi:10.2514/1.37390

Cited by 43 publications

(11 citation statements)

References 17 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Catalano et al 39 reported that SST k - ω model shows the best compromise between the physical modeling capabilities and the computational cost. Moreover, Slater et al 42 concluded that both SA and SST k - ω models are able to predict the intake performance parameters within the experimental uncertainty level.…”

Section: Introductionmentioning

confidence: 99%

Computation of viscous flow characteristics of a supersonic intake using eddy-viscosity turbulence models

Pattnaik

Rajan

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Results of numerical investigation of flow and performance characteristics of a rectangular supersonic intake experimentally tested at Mach number of 4.03 are presented. The viscous flowfield has been obtained by solving Favre averaged Navier–Stokes equations with two eddy viscosity turbulence models, namely, Mentor’s baseline (BSL) k-ω and shear stress transport (SST) k-ω models. In addition, the effect of wall temperature conditions as well as several configurations of cowl and isolator are simulated to validate the computational methodology. The analysis has been carried out at a freestream Mach number of 4.03 and 0° angle-of-attack, corresponding to a unit Reynolds number of about 6.9×107 m−1. The predicted boundary-layer and the wall static pressure distribution using SST k-ω model shows better agreement with the experimental data compared to the BSL model and hence indicates superior capability to capture the onset and the amount of flow separation due to SWBLIs. Moreover, the terminal shock structure at different operating modes as well as the “unstart because of SWBLIs” is predicted quite accurately using the model. The wall temperature condition is found to have a strong effect on the amount of flow separation at the cowl and the subsequent interactions. Further, the results show that the sidewalls have a marginal effect on the centerline wall static pressure, though a three-dimensional flowfield with two stream-wise vortices are observed close to it as a result of the swept SWBLIs of the cowl shock with the sidewall boundary-layer leading to a higher loss in performance.

show abstract

Section: Introductionmentioning

confidence: 99%

Computation of viscous flow characteristics of a supersonic intake using eddy-viscosity turbulence models

Pattnaik

Rajan

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Recently, a model has been fabricated to simulate porous bleed systems. 8 Effects of the slot bleed geometry on an axisymmetric supersonic air intake have been also explored. 9 Interconnected throat suction and pre-entry injection slots were used and it was shown that higher pressure recoveries and stable subcritical shock position could be achieved.…”

Section: Introductionmentioning

confidence: 99%

Performance investigation of a supersonic air intake in the presence of the boundary layer suction

Soltani

Sepahi-Younsi

Daliri

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The performance of a supersonic mixed compression air intake has been investigated experimentally. The intake is of axisymmetric one and has been designed for a free stream Mach number of 2.0. The present work has two main goals, first to investigate the performance of the intake without boundary layer bleed at design and at off-design conditions and second to study the effects of a bleed slot on the intake performance. The intake has been tested at free stream Mach numbers of 1.8, 2.0, and 2.2 and at zero degrees angle of attack. Total pressure recovery, mass flow ratio, and flow distortion have been selected to assess the intake performance. The bleed slot is located upstream of the intake throat perpendicular to the compression ramp surface. The suction is applied by the natural pressure difference between the entrance and the exit faces of the bleed duct. Results show that applying the boundary layer suction upstream of the intake throat can considerably improve the intake performance at its design and off-design conditions while it does not affect the intake mass flow rate.

show abstract

“…Additionally, the performance of the inlet decrease greatly and perhaps work instable at the off-design conditions. 3 Up to now, the researchers have proposed varieties of improved methods to improve inlet’s comprehensive performance, such as variable geometry, 4,5 porous bleeding, 6 boundary layer suction, 7 MHD control method, 9 plasma control method, 9 slot bleeding, 1,10–26 isentropic expansion arc surface 26,27 and so on. Among these control methods, the slot bleeding and isentropic expansion arc surface are the most simple and efficient improved methods, because they do not need any additional energy or control devices.…”

Section: Introductionmentioning

confidence: 99%

Comparison research of two different improved methods in the 2D hypersonic inlet’s design

Yang

Luo

Huang

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The article mainly employed the numerical simulation method to conduct the 2D hypersonic inlet performance research. In this study, the numerical simulation method that includes a two-equation turbulence model was validated through the test case firstly. For the purpose of oppressing unstart phenomena, extending operating range and improving comprehensive performance of the inlet, the bleeding system and isentropic expansion arc surface were applied to the inlet, respectively. Different kinds of configurations were designed through changing the length of the bleeding or changing the radius of the arc surface. The influence of the bleeding and isentropic expansion arc surface on the 2D hypersonic inlet was analyzed systematically based on different objective parameters. The calculative results show that the bleeding system with appropriate value of the length can improve comprehensive performance of hypersonic inlet remarkably either on the design point or the off-design points, though it has a very small negative impact on the inlet in terms of the mass flow ratio coefficient. As for isentropic expansion arc surface, it can improve the inlet's performance at the design point on the conditions that the radius of isentropic expansion arc surface has an appropriate value. But it has much more disadvantages over the basic configuration reversely when it comes to the off-design conditions or the large size of the radius of isentropic expansion arc surface.

show abstract

Modeling of Fixed-Exit Porous Bleed Systems for Supersonic Inlets

Cited by 43 publications

References 17 publications

Computation of viscous flow characteristics of a supersonic intake using eddy-viscosity turbulence models

Computation of viscous flow characteristics of a supersonic intake using eddy-viscosity turbulence models

Performance investigation of a supersonic air intake in the presence of the boundary layer suction

Comparison research of two different improved methods in the 2D hypersonic inlet’s design

Contact Info

Product

Resources

About