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Extensive experimental investigations of transonic flow development over the payload region of a generic launch vehicle model have been carried out. The effect of changing the semi-nose cone angle in the range of \(15^\circ \) to \(25^\circ \) is one of the problems studied. For angles of \(20^\circ \) – \(25^\circ \) and certain combinations of Mach number and angle of attack, a large amplification of pressure fluctuations was observed. This paper reports analyses of pressure sensor data and high-speed shadowgraph images based on the dynamic mode decomposition (DMD) technique to better understand the phenomena. This technique holds significance in flow diagnostics and the prospective estimation tools of complex nonlinear flow phenomena.

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Exploring Dynamic Mode Decomposition Technique for Analyses of Transonic Shock Oscillations on a Typical Launch Vehicle Model

  • 会议论文

  • 发表日期：

    2025年

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  • D. B. Singh,
  • Gireesh Yanamashetti,
  • G. K. Suryanarayana,
  • G. Jagadeesh

摘要

Extensive experimental investigations of transonic flow development over the payload region of a generic launch vehicle model have been carried out. The effect of changing the semi-nose cone angle in the range of \(15^\circ \) to \(25^\circ \) is one of the problems studied. For angles of \(20^\circ \) – \(25^\circ \) and certain combinations of Mach number and angle of attack, a large amplification of pressure fluctuations was observed. This paper reports analyses of pressure sensor data and high-speed shadowgraph images based on the dynamic mode decomposition (DMD) technique to better understand the phenomena. This technique holds significance in flow diagnostics and the prospective estimation tools of complex nonlinear flow phenomena.