Global Visualization of Compressible Swept Convex-Corner Flow Using Pressure-Sensitive Paint

Chung, Kung Ming; Huang, Yi

doi:10.3390/aerospace8040106

Cited by 5 publications

(1 citation statement)

References 19 publications

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“…For example, the present of supersonic SWBLIs on the deflected control surface might influence the performance of this high-lift device. Chung et al [1] studied the related simplified compressible swept convex-corner flow with different convex-corner angles and swept angles. They also installed a vortex generator at the corner to study its effect on SWBLIs [2].…”

Section: Introductionmentioning

confidence: 99%

Uncertainty Analysis of Parameters in SST Turbulence Model for Shock Wave-Boundary Layer Interaction

Zhang

Zeng

et al. 2022

Aerospace

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Shock wave-boundary layer interactions (SWBLIs) have a tremendous influence on the performance of hypersonic vehicles. For the numerical simulation of such engineering flows, Reynolds averaged Navier-Stokes (RANS) still occupies an irreplaceable role. However, parameters of turbulence models in RANS have substantial uncertainties, which impact the reliability of simulation results. Thus, the aim of the present study is to conduct an uncertainty analysis on parameters in the shear-stress transport (SST) turbulence model for the simulation of SWBLIs. In the current work, uncertainty quantification was performed first. A surrogate model was constructed by the non-intrusive polynomial chaos (NIPC) method to propagate uncertainties from model parameters to the quantities of interests (QoIs) and quantify them. In the subsequent sensitivity analysis, the key parameters were identified for such flow by calculating the Sobol index of each parameter for various QoIs. The results indicate that uncertainties of model parameters led to non-negligible uncertainties in those QoIs, particularly in skin friction and wall heat flux. The parameters α1, σω1, β1 were identified as primary contributors through the sensitivity analysis. Moreover, the specific effects of the three parameters on the flow prediction were analyzed by changing the parameters’ values separately.

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Section: Introductionmentioning

confidence: 99%

Uncertainty Analysis of Parameters in SST Turbulence Model for Shock Wave-Boundary Layer Interaction

Zhang

Zeng

et al. 2022

Aerospace

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Pressure-sensitive paint measurements on the cavity with passive control devices under transonic flow

Ouyang,

Liao,

Hsu

et al. 2023

Journal of Mechanics

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In this study, the pressure-sensitive paint (PSP) technique, specifically the mesoporous-particle-based PSP, was employed to compare rectangular cavities with varying length-to-depth ratios (L/D) and different trailing edge shapes under transonic conditions. By utilizing PSP, comprehensive and quantitative pressure data were obtained, enabling the simultaneous observation of surface flow field distribution. The results obtained using PSP were found to be consistent with those obtained from conventional pressure sensors. The study revealed that the pressure distribution within the cavities changed with increasing L/D, and cavities with different trailing edge shapes demonstrated a reduction in pressure at the bottom region. Furthermore, the comparison of results obtained through the oil flow method corroborated the PSP findings, indicating that a beveled or sawtooth-shaped trailing edge of the cavity induced air flow deflection, effectively disrupting the upstream shear flow structure and altering the pressure distribution at the cavityʼs bottom.

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Downstream influence of turbulent flow past vortex generators

Huang,

Chung,

Chung

et al. 2023

Journal of Mechanics

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Vortex generators (VGs) are typically positioned upstream of a boundary layer separation region. Their effectiveness depends on incoming flow conditions (Mach number, Reynolds number, and boundary layer characteristics), geometrical configuration (vane or ramp, height, width, and angle of incidence), and spacing. Device-induced vortices and following decay allow VGs to be used as a passive control device. This study uses pressure-sensitive paint to determine the global surface pressure pattern for a flat plate flow in the presence of VGs (counter-rotating vanes, co-rotating vanes and ramps). The freestream Mach number is 0.64 and 0.83. The ratio between the height of the VGs and the incoming boundary layer thickness is 0.2, 0.5, and 1.0. The standard deviation in the spanwise pressure in the streamwise direction is used to determine the downstream influence of turbulent flow past VGs. Increasing the height of VGs causes device-induced vortices to propagate farther downstream.

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Global Visualization of Compressible Swept Convex-Corner Flow Using Pressure-Sensitive Paint

Cited by 5 publications

References 19 publications

Uncertainty Analysis of Parameters in SST Turbulence Model for Shock Wave-Boundary Layer Interaction

Uncertainty Analysis of Parameters in SST Turbulence Model for Shock Wave-Boundary Layer Interaction

Pressure-sensitive paint measurements on the cavity with passive control devices under transonic flow

Downstream influence of turbulent flow past vortex generators

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