Abstract
Spherically blunted cones are commonly utilized as re-entry or entry capsules. Depending on the cone angle, the shock shape is either dominated by the spherical nose or the conical part. In flight a transition between these two situations might occur, and this can result in undesirable effects on the aerodynamic stability. To understand the shock shape transition behaviour in more detail, a systematic numerical and experimental study is ongoing. In the present article, the influence of vibrational non-equilibrium compared to frozen flow is discussed for sphere-cone configurations at zero-degree angle of attack.
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Martinez Schramm, J., Hannemann, K., Hornung, H.G. (2019). Shock Shape Transition on Spherically Blunted Cones in Hypersonic Flows. In: Sasoh, A., Aoki, T., Katayama, M. (eds) 31st International Symposium on Shock Waves 2. ISSW 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-91017-8_33
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DOI: https://doi.org/10.1007/978-3-319-91017-8_33
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