A combined criteria-based method for hypersonic three-dimensional boundary layer transition prediction

Zhou, Lingjun; Zhao, Rui; Li, Renfu

doi:10.1016/j.ast.2017.12.002

Cited by 21 publications

(4 citation statements)

References 30 publications

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“…Nowadays, the FDD methods have been extended to the fields of unsteady flow, 11,17 aerodynamic optimization, [18][19][20][21] engine thrust and drag analysis, 10,[22][23][24] laminar aerodynamic analysis 25,26 and mesh refinement. 27 However, the problems on the robustness and convenience of the FDD method are still unfixed.…”

Section: Introductionmentioning

confidence: 99%

Far-field drag decomposition using hybrid formulas and vorticity based area sensors

Qiao

Sun

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Numerical simulation of flow-field has become an indispensable tool for aerodynamic design. Usually, wall surface integration is a tool used to calculate values of pressure drag and skin friction drag, but the aerodynamic mechanism of drag production is still confusing. In present work, in order to decompose the total drag into viscous drag, wave drag, induced drag, and spurious drag, a far-field drag decomposition (FDD) method is developed. This method depends on axial velocity defect and area sensor functions. The present work proposes three hybrid formulas for velocity defect to tackle the negative square root issue by analyzing the existing axial velocity defect formulas. For dealing with the issue of detection failure for near-wall cells, a novel vorticity based viscous area sensor function is proposed. The new area sensor function is also independent of the turbulence model, which ensures easy application to general simulation methods for flow-field. Three tests cases are there to validate the proposed FDD method. The three dimensional transonic CRM test case shows that the present improvement is crucial for accurate drag decomposition. Excellent agreement between total decomposed drags and results from the near-field method or experimental data further confirms the correctness.

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Section: Introductionmentioning

confidence: 99%

Far-field drag decomposition using hybrid formulas and vorticity based area sensors

Qiao

Sun

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…It was extended to hypersonic transitional flows dominated by the first and second mode, and laminar separation in 2017 [17]. Wang and Fu [18] and Wang and Fu [19] also combined these models between 2009 and 2012 to design their k − ω − γ local model for hypersonic transitional flows, which was improved recently by Zhou et al ([20], [21], [22]).…”

Section: Nomenclaturementioning

confidence: 99%

Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Chanteux

Bégou

Deniau

et al. 2022

AIAA AVIATION 2022 Forum

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“…However, it cannot accurately predict transitions in three-dimensional high-speed flows owing to the strong crossflow and Mack's 2 nd mode instabilities, respectively [34][35][36]. To address these limitations of correlationbased models, several other transition models have been developed [37][38][39]. However, correlation-based models offer several advantages, and therefore, the demand for their improvement and development continues to increase.…”

Section: Introductionmentioning

confidence: 99%

Comparative Assessment of Modified $γ$ - ${Re}_{θ t}$

Kang

Shin

Park

et al. 2021

International Journal of Aerospace Engineering

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The selection of an appropriate turbulence/transition model is critical when simulating the hypersonic flows based on the Reynolds-averaged Navier–Stokes (RANS) equation. In particular, a deep understanding of the validity, reliability, and limitations of existing models is an essential prerequisite to facilitate their further development. This paper reports on the assessment of two models dedicated to hypersonic boundary layer transition analysis. Both models are compared with two other models that are widely used in this field. The double ramp and shock wave laboratory scramjet intake cases are used for the validation and evaluation of the predictive performance of both models via comparison against experimental data. The results reveal that the appropriate selection of the transition model is critical to the attainment of accurate results. Moreover, the forebody of the scramjet combustion propulsion-01 (SCP-01) flight vehicle, which is a research model, is analyzed as a case study. The air intake performance of the SCP-01, as predicted by four models, is compared and analyzed at different flight altitude and Mach number conditions. The results reveal that the accuracy of the prediction of boundary layer and separated flow transitions significantly affects the flow field and corresponding air intake performance. Furthermore, the uncertainty of results obtained using the two models increases significantly with an increase in altitude. Finally, the reliability and limitations of the transition models considered in this study are examined.

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A combined criteria-based method for hypersonic three-dimensional boundary layer transition prediction

Cited by 21 publications

References 30 publications

Far-field drag decomposition using hybrid formulas and vorticity based area sensors

Far-field drag decomposition using hybrid formulas and vorticity based area sensors

Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Comparative Assessment of Modified $γ$ - ${Re}_{θ t}$

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A combined criteria-based method for hypersonic three-dimensional boundary layer transition prediction

Cited by 21 publications

References 30 publications

Far-field drag decomposition using hybrid formulas and vorticity based area sensors

Far-field drag decomposition using hybrid formulas and vorticity based area sensors

Construction and Application of Transition Prediction Databased Method for 2nd Mode on Sharp Cone

Comparative Assessment of Modified γ - Re θ t

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Product

Resources

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Construction and Application of Transition Prediction Databased Method for 2^nd Mode on Sharp Cone

Comparative Assessment of Modified $γ$ - ${Re}_{θ t}$