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Hypersonic boundary-layer transition on a flared cone

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Abstract

Transition on a flared cone with zero angle of attack was studied in our newly established Mach 6 quiet wind tunnel (M6QT) via wall pressure measurement and flow visualization. High-frequency pressure transducers were used to measure the second-mode waves’ amplitudes and frequencies. Using pulsed schlieren diagnostic and Rayleigh scattering technique, we got a clear evolution of the second-mode disturbances. The second-mode waves exist for a long distance, which means that the second-mode waves grow linearly in a large region. Strong Mach waves are radiated from the edge of the boundary layer. With further development, the second-mode waves reach their maximum magnitude and harmonics of the second-mode instability appear. Then the disturbances grow nonlinearly. The second modes become weak and merge with each other. Finally, the nonlinear interaction of disturbance leads to a relatively quiet zone, which further breaks down, resulting in the transition of the boundary layer. Our results show that transition is determined by the second mode. The quiet zone before the final breakdown is observed in flow visualization for the first time. Eventual transition requires the presence of a quiet zone generated by nonlinear interactions.

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Authors and Affiliations

  1. Department of Aeronautics & Astronautics, College of Engineering, Peking University, 100871, Bei**g, China

    Chuan-Hong Zhang, Qing Tang & Cun-Biao Lee

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  1. Chuan-Hong Zhang
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  2. Qing Tang
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  3. Cun-Biao Lee
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Correspondence to Cun-Biao Lee.

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Zhang, CH., Tang, Q. & Lee, CB. Hypersonic boundary-layer transition on a flared cone. Acta Mech Sin 29, 48–54 (2013). https://doi.org/10.1007/s10409-013-0009-2

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  • DOI: https://doi.org/10.1007/s10409-013-0009-2

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