Experimental research on the influence of turbulence intensity on boundary layer transition in Mach 3 supersonic flow

LI Meng; ZHAO Huiyong; YUAN Qiang; CHEN Li; MU Jinhe

doi:10.11729/syltlx20220087

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LI M，ZHAO H Y，YUAN Q，et al. Experimental research on the influence of turbulence intensity on boundary layer transition in Mach 3 supersonic flow[J]. Journal of Experiments in Fluid Mechanics, 2022，36（X）：1-9. doi: 10.11729/syltlx20220087

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Experimental research on the influence of turbulence intensity on boundary layer transition in Mach 3 supersonic flow

doi: 10.11729/syltlx20220087

LI Meng^1
,,
ZHAO Huiyong²,
YUAN Qiang¹,
CHEN Li^{1, 2
,
,},
MU Jinhe¹

1.
Facility Design and Instrumentation Institute, China Aerodynamics Researchand Development Center, Mianyang,　621000, China
2.
Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamic Institute， China Aerodynamics Research and Development Center, Mianyang,　621000, China

Received Date: 2022-09-05
Accepted Date: 2022-10-08
Rev Recd Date: 2022-09-26

Available Online: 2022-11-15

Abstract

Abstract

There is still a shortage of the experimental research of boundary layer transition in compressible flows nowadays due to the difficulty in measuring the turbulence intensity. Aiming at studying the influence of the turbulence intensity on supersonic boundary layer transition, a plate model is tested in a blow-down facility （FL-24y of CARDC） at Mach 3. The turbulence intensity of the flow is changed by adjusting the arrangements in the stabilization section of the wind tunnel, which covers a range from 0.82% to 1.63%. The turbulence intensity is measured by interferometric Rayleigh scattering, while the boundary layer transition is derived by infrared thermography. The CFD simulation of the plate model transition is conducted based on the γ-Re_θ transition model. The results show that the transition onset position （F_onset） and transition end position （F_length） obtained by the experiment and the simulation agree well, with the maximum relative error coefficient of 2% in F_onset and of 5% in F_length, which provides support to gain a deeper insight into the boundary layer transition mechanism in supersonic flows.
- turbulence intensity,
- boundary layer transition,
- infrared thermography,
- interferential Rayleigh scattering,
- supersonic flow

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References(22)

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