Numerical investigations of the slot blowing technique on the hypersonic vehicle for drag reduction

Mo, Fan; Su, Wei; Gao, Zhenxun; Du, Chang; Lee, Chun‐Hian

doi:10.1016/j.ast.2022.107372

Cited by 8 publications

(3 citation statements)

References 25 publications

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“…The reliability of ACANS has been verified by numerous numerical simulation studies (Mo et al. 2022, 2023). The boundary conditions for numerical simulation in this paper are shown in table 1, where the wall temperature ratio is defined as the ratio of the wall temperature to the adiabatic wall temperature, and implies a cold wall.…”

Section: Laws Of the Wall For Hlblsmentioning

confidence: 86%

“…For compressible turbulent boundary layers (CTBLs), the effective wall function method has been developed to relax the restrictions on y 1 in simulating c f and q w (Wilcox 2006), which uses the laws of the wall to represent the distribution of velocity and temperature, and obtains c f and q w indirectly, instead of resolving the near-wall region of CTBLs. Based on the incompressible wall function, Nichols & Nelson (2004) first introduced the compressible velocity log law (White 1991) and temperature-velocity relation (Walz 1969), then proposed a compressible wall function, which is effective uniformly in the inner layer of CTBLs and involves a compressibility effect, thus making it possible to use the wall function method to obtain c f and q w in CTBLs. Subsequently, Gao, Jiang & Lee (2013) revised the parameters in the laws of the wall used by Nichols according to theoretical analysis and numerical experiments, and achieved a more accurate coupling of wall function with computational fluid dynamics (CFD) codes.…”

Section: Introductionmentioning

confidence: 99%

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A new wall function method for hypersonic laminar boundary layers

Mo,

Gao

2024

J. Fluid Mech.

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A new wall function method for hypersonic laminar boundary layers (HLBLs) is proposed to reduce the near-wall grid dependence of skin friction $c_f$ and wall heat flux $q_w$ in numerical simulations, aiming for fast and accurate predictions. First, an analytic laminar velocity law of the wall is derived, which achieves a universal scaling of the near-wall velocity of HLBLs. Then an accurate temperature–velocity relation is deduced by introducing the general recovery factor to address the invalidation of the Walz relation under the cold wall effect. Based on the laminar laws of the wall, a new wall function method for HLBLs is proposed. To avoid introducing the boundary layer edge quantities, the laminar laws of the wall are reformed by modifying the outer boundary conditions of the differential equation in deriving the temperature–velocity relation. Unlike the wall function method in turbulence, the new wall function obtains directly the accurate $c_f$ and $q_w$ by post-processing without being involved in the simulation iteration. The numerical experiments of a Mach 8 HLBL over the flat plate show that effectively, the new wall function can enlarge the distance of the first grid point off the wall $\Delta y_1$ from $10^{-6}$ m to $10^{-3}$ m, which brings a 50 times enhancement of the simulation efficiency. Meanwhile, the simulation errors of $c_f$ and $q_w$ of the mesh with $\Delta y_1=10^{-3}$ m are reduced significantly from 24.2 % and 18.5 % to 0.5 % and 0.1 %, respectively. Due to the new wall function removing the boundary layer edge quantities, success is also achieved under the curved walls.

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Section: Laws Of the Wall For Hlblsmentioning

confidence: 86%

Section: Introductionmentioning

confidence: 99%

A new wall function method for hypersonic laminar boundary layers

Mo,

Gao

2024

J. Fluid Mech.

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“…Experiments on flat boundary layers have proved that drag reduction can be achieved by about 50% in subsonic and even supersonic flow. Fan [4] carried out a numerical simulation of slotted blowing flow control and applied it to a typical lifting body.…”

Section: Introductionmentioning

confidence: 99%

Research on Drag Reduction and Heat Prevention of Hypersonic Vehicle Combined Model with Reverse Jet and Slot Blowing

Fang²,

Guo³

et al. 2023

J. Phys.: Conf. Ser.

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A novel strategy combining reverse jet with slotted blowing is proposed in this paper, and two-dimensional (RANS) is used to numerically investigate the flow characteristics of a reverse jet. The numerical results show the jet from the aircraft head ejects backward, pushing the shock away and reducing aerodynamic heating and shock wave resistance. The jet from the middle slot ejects backward and the effective solution reduces the viscous resistance of the fuselage. This new strategy not only further reduces the total resistance but also provides good thermal protection for the aircraft. Compared with the aircraft model, the stagnation point temperature and resistance are reduced by 25.0% and 28.0%, respectively, with the addition of multiple jets.

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