### Abstract

Original language | English |
---|---|

Title of host publication | Shock Wave Interactions |

Pages | 355-366 |

Publication status | Published - 2018 |

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### Cite this

*Shock Wave Interactions*(pp. 355-366)

**Shock reflection in axisymmetric internal flows.** / Shoesmith, Ben; Mölder, Sannu; Ogawa, Hideaki; Timofeev, Evgeny.

Research output: Chapter in Book/Report/Conference proceeding › Chapter (peer-reviewed)

*Shock Wave Interactions.*pp. 355-366.

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TY - CHAP

T1 - Shock reflection in axisymmetric internal flows

AU - Shoesmith, Ben

AU - Mölder, Sannu

AU - Ogawa, Hideaki

AU - Timofeev, Evgeny

PY - 2018

Y1 - 2018

N2 - The flow downstream of an axisymmetric conical shock wave, with a downstream pointing apex, can be predicted by solving the Taylor-Maccoll equations. Previous research, however, has suggested that these theoretical flowfields are not fully realisable in practice, and that a Mach reflection forms towards the centreline of the flow. This phenomenon is investigated for the case where the freestream Mach number is 3.0 and the shock angle is 150֯ . A range of complementary prediction techniques that include the solution to the Taylor-Maccoll equations, the method of characteristics, curved shock theory and CFD, are used to gain insight into this flow. The case where a cylindrical centrebody is placed along the axis of symmetry is studied for several values of centrebody radius that are expected to produce regular reflection at the centrebody surface. An analysis of pressure gradients suggests that the flowfield downstream of the reflected shock does not contribute to the process of transition from regular to Mach reflection at these conditions.

AB - The flow downstream of an axisymmetric conical shock wave, with a downstream pointing apex, can be predicted by solving the Taylor-Maccoll equations. Previous research, however, has suggested that these theoretical flowfields are not fully realisable in practice, and that a Mach reflection forms towards the centreline of the flow. This phenomenon is investigated for the case where the freestream Mach number is 3.0 and the shock angle is 150֯ . A range of complementary prediction techniques that include the solution to the Taylor-Maccoll equations, the method of characteristics, curved shock theory and CFD, are used to gain insight into this flow. The case where a cylindrical centrebody is placed along the axis of symmetry is studied for several values of centrebody radius that are expected to produce regular reflection at the centrebody surface. An analysis of pressure gradients suggests that the flowfield downstream of the reflected shock does not contribute to the process of transition from regular to Mach reflection at these conditions.

M3 - Chapter (peer-reviewed)

SP - 355

EP - 366

BT - Shock Wave Interactions

ER -