Flow features of shock-induced combustion around projectile traveling at hypervelocities

Akiko Matsuo, Kozo Fujii, Toshi Fujiwara

Research output: Contribution to journalArticlepeer-review

65 Citations (Scopus)


The shock-induced combustion with periodic unsteadiness around a projectile fired into hypersonic flows is numerically studied. The mechanism of periodic unsteadiness is clarified using an x-t diagram of the flow variable on the stagnation streamline. The frequencies of the periodic unsteadiness obtained quantitatively agree with the experimental observations. The key parameters which are responsible in triggering the instability and in determining the frequency of the periodic unsteadiness are discussed by using the time integration of the species equations. The result indicates that the key parameters are induction time, heat release, and concentration of the heat release. The induction tune is a key parameter for the frequency of the unsteadiness. The concentration of heat release is important for the unsteadiness itself. Total energy creating the compression waves depends on the amount of heat release itself. All of these features are recognized in a simple zero-dimensional analysis.

Original languageEnglish
Pages (from-to)1056-1063
Number of pages8
JournalAIAA journal
Issue number6
Publication statusPublished - 1995 Jun

ASJC Scopus subject areas

  • Aerospace Engineering


Dive into the research topics of 'Flow features of shock-induced combustion around projectile traveling at hypervelocities'. Together they form a unique fingerprint.

Cite this