Numerical investigation of shock-induced combustion with unsteady oscillation around hypervelocity conical projectile

Kazushige Maeda, Akiko Matsuo

研究成果: Conference contribution

1 被引用数 (Scopus)


Shock-Induced Combustion around hypervelocity conical projectile was numerically investigated using two-dimensional axisymmetric and three-dimensional Euler equations. For the calculation conditions used in this study, the shock wave around a conical projectile is attached in the case of nonreacting flow. Periodic oscillatory combustion and unsteady combustion around a conical body are observed in two-dimensional simulations. The twodimensional calculation results reveal that the propagation of triple point structure generates the dynamic behavior of oscillatory combustion. The oscillatory combustion for the large diameter case becomes unsteady because plural triple points are randomly formed. Parametric studies for the diameter and the induction length are conducted, and the results reveal the importance of lcone/lOSW ind, showing the geometry vs. the induction effect, and lcone/lOSW reac, showing the geometry vs. the exothermic effect, for the combustion regime. Threedimensional calculation is conducted to confirm the three-dimensional behavior of the combustion wave for both periodic and unsteady regimes. The calculation results indicate that the Shock-Induced Combustion around a conical body is essentially axisymmetric. The re-attachment of an oblique shock wave to the tip of the conical projectile during the unsteady oscillation is the key phase to keep the axisymmetry in this phenomenon because this process removes a disturbance on the reaction front.

ホスト出版物のタイトル53rd AIAA Aerospace Sciences Meeting
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
出版ステータスPublished - 2015
イベント53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
継続期間: 2015 1月 52015 1月 9


Other53rd AIAA Aerospace Sciences Meeting, 2015
国/地域United States

ASJC Scopus subject areas

  • 航空宇宙工学


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