Numerical study of active flow control over a hypersonic backward-facing step using supersonic jet in near space

Guo, Gaofeng; Hong, Liu; Zhang, Bin

doi:10.1016/j.actaastro.2016.12.035

Cited by 23 publications

(4 citation statements)

References 32 publications

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“…Relevant conservation equations in vectoral form are given between Eqns. ( 5)-( 7) and then their expanded versions are given between ( 8)- (11) [67]. Details of derivation differential elliptic forms of the governing equations from vector forms are explained in the given reference [67].…”

Section: Theoretical Approach and Methodsmentioning

confidence: 99%

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Numerical Forced Convection Heat Transfer of Nanofluids over Back Facing Step and Through Heated Circular Grooves

Abdulkarim¹,

Eleiwi²,

Tahseen³

et al. 2021

MMEP

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Backward facing step arrangement is a classical case for fluid dynamics and heat transfer research. It is well characterized and therefore, used for benchmarking. However, ongoing studies reveal that the geometry also provide advantages in industry, especially in combustion and burners. This work utilizes computational fluid dynamics to investigate a specific laminar back facing step flow heat transfer case. Aluminium oxide nano particles are considered as an additive to water base fluid, forming nanofluid with different volumetric concentrations. Laminar flow passes a back facing step and encounters three circular grooves at bottom surface. All surfaces are adiabatic except the grooves. Constant surface temperature applies to the grooves. According to the simulation results, a separation bubble after back facing step and a reattachment point occur. Grooves alter expected wake due to physical and thermal interference. Investigation parameters are nano-particle concentration and Reynolds number. Reynolds number changes between 10 and 250. Nano particle volume fraction percentage changes between 2 and 6 percent. Sectional heating downstream of the step poses interesting heat flux in the presence of Aluminium oxide nano-particle concentrations. There is a pseudo-linear relationship between parameters and heat transfer. Combined effects of enhanced thermal conductivity and secondary flow structures are seen. As expected, thermal convection increases as flow velocity and nano-particle concentrations increase. Heat flux and accordingly Nusselt number are highly affected from Reynolds number since flow structure changes dramatically. Also, direct proportion is seen between nano-particle concentration and enhanced convection.

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Section: Theoretical Approach and Methodsmentioning

confidence: 99%

“…There are shock waves due to impingement of the flow at the reattachment, and redeveloping boundary layer under the shock wave. Guo et al [11] investigated hypersonic flow over BFS numerically by Direct Simulation Monte Carlo (DSMC) method for near space engineering. They identified very different behaviour as altitude gets high.…”

Section: Introductionmentioning

confidence: 99%

Numerical Forced Convection Heat Transfer of Nanofluids over Back Facing Step and Through Heated Circular Grooves

Abdulkarim¹,

Eleiwi²,

Tahseen³

et al. 2021

MMEP

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“…The following numerical simulations are performed by using the DSMC code developed by Liu's team from Shanghai Jiao Tong University, which has been validated with some 064702-2 typical benchmark cases in our recent researches. [24,[26][27][28][29] However, to estimate the applicability of the DSMC code for the micro-channel gas flow, the case of a 2D micro-channel (for the geometry of the micro-channel and free stream conditions, please refer to Ref. [1]), in which the simulation data from different researchers are detailed, is used to perform our DSMC simulation to provide the quantitative calculation results for the code validation.…”

Section: Validation Of the Dsmc Codementioning

confidence: 99%

“…The micro-perspective and statistical property are two distinct features of the DSMC method. The working process of the DSMC simulation can be summarized as in the following steps: [24] (i) reading the grid data and recording the information about the boundary conditions; (ii) initializing the flow field and calculating the entering number of simulating molecules; (iii) simulating the molecules' motion and interaction with boundary; (iv) indexing all of the simulating molecules; (v) simulating the molecules' probabilistic selection and collision with each other; (vi) sampling the mesh cell and wall information and repeating steps (iii)-(vi) until the flow field reaches a steady state; and (vii) writing out the information about the flow field and wall.…”

Section: Dsmc Introductionmentioning

confidence: 99%

Flow characteristics of supersonic gas passing through a circular micro-channel under different inflow conditions*

et al. 2019

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Gas flow in a micro-channel usually has a high Knudsen number. The predominant predictive tool for such a micro-flow is the direct simulation Monte Carlo (DSMC) method, which is used in this paper to investigate primary flow properties of supersonic gas in a circular micro-channel for different inflow conditions, such as free stream at different altitudes, with different incoming Mach numbers, and with different angles of attack. Simulation results indicate that the altitude and free stream incoming Mach number have a significant effect on the whole micro-channel flow field, whereas the angle of attack mainly affects the entrance part of micro-channel flow field. The fundamental mechanism behind the simulation results is also presented. With the increase of altitude, thr free stream would be partly prevented from entering into micro-channel. Meanwhile, the gas flow in micro-channel is decelerated, and the increase in the angle of attack also decelerates the gas flow. In contrast, gas flow in micro-channel is accelerated as free stream incoming Mach number increases. A noteworthy finding is that the rarefaction effects can become very dominant when the free stream incoming Mach number is low. In other words, a free stream with a larger incoming velocity is able to reduce the influence of the rarefaction effects on gas flow in the micro-channel.

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Analysis and reduction of skin-friction in a rocket-based combined-cycle engine flow path operating from Mach 1.5 to 6.0

Wang

Yan

et al. 2018

Acta Astronautica

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Numerical study of active flow control over a hypersonic backward-facing step using supersonic jet in near space

Cited by 23 publications

References 32 publications

Numerical Forced Convection Heat Transfer of Nanofluids over Back Facing Step and Through Heated Circular Grooves

Numerical Forced Convection Heat Transfer of Nanofluids over Back Facing Step and Through Heated Circular Grooves

Flow characteristics of supersonic gas passing through a circular micro-channel under different inflow conditions*

Analysis and reduction of skin-friction in a rocket-based combined-cycle engine flow path operating from Mach 1.5 to 6.0

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