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Experimental Study on Unsteady Characteristics of Shock and Turbulent Boundary Layer Interactions

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Abstract—

In this paper, the experimental study on the shock wave and turbulent boundary layer interactions was performed in the Mach 3.4 supersonic low-noise wind tunnel. The angle of the shock generator was θ = 15°, and the unit Reynolds number of 6.30 × 106 m–1. The wall temperature and pressure distribution during the disturbance process of the shock wave and the turbulent boundary layer were obtained based on the temperature-sensitive paints technique and the flush air data sensing system, and the basic flow field of the interactions region was partitioned. Meanwhile, based on the nano-tracer planar laser scattering technique, and the instantaneous fine structures in the interaction region were obtained and the spatiotemporal evolution characteristics of the flow structure were analyzed. The flow visualization images showed that the oscillation position of the induced shock wave satisfied the normal distribution. Compared with the flow visualization images and the temperature results, the correlation between the flow structure of the interactions region and the wall temperature change was obtained. At the same time, the wall fluctuation pressure of the center surface of the shock wave and turbulent boundary layer interactions region was measured by the high-frequency pulsating pressure sensor. The power spectrum density results showed that under the action of the shock wave incident by the shock generator, there were two characteristics frequency signal of 12 and 30 kHz in the induced shock oscillation interval. For the signal of 12 kHz, the frequency value and the amplitude were increased from the turbulent boundary layer to the separation bubble, and the oscillation energy of the induced shock wave was enhanced. The amplitude of the peak signal of each measurement point gradually decreased from the separation bubble to the reattachment zone, and the energy was gradually attenuated. For the high frequency signal of 30 kHz, the frequency variation of each channel was relatively small, relatively stable, and the energy was concentrated.

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Funding

This work was supported by the National Project for Research and Development of Major Scientific Instruments of China, project no. 11527802, the Major Research Plan of the National Natural Science Foundation of China, project nos. 91752102 and 11832018, and the National Key Research and Development Plan of China, project no. 2016YFA0401200.

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Authors and Affiliations

  1. College of Aerospace Science and Engineering, National University of Defense Technology, No. 109, Deya Road, 410073, Changsha, Hunan, China

    X. G. Lu, S. H. Yi, L. He, D. D. Gang & H. B. Niu

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  1. X. G. Lu
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  2. S. H. Yi
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  3. L. He
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  4. D. D. Gang
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  5. H. B. Niu
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Correspondence to X. G. Lu.

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Lu, X.G., Yi, S.H., He, L. et al. Experimental Study on Unsteady Characteristics of Shock and Turbulent Boundary Layer Interactions. Fluid Dyn 55, 566–577 (2020). https://doi.org/10.1134/S0015462820030088

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