Aerodynamic Vibrations Caused by a Vortex Ahead of Hemisphere in Supersonic Flow

  • Takafumi Kawamura
  • Toshiharu Mizukaki
Conference paper


Parachutes are often used for planetary-entry and re-entry. Most of cases, parachutes are deployed at supersonic speed. Therefore, it is necessary to obtain aerodynamic characteristics at supersonic speed. However parachutes have wrinkles and seams. They make it difficult to study aerodynamic characteristics of the parachute shape. Therefore, experimental studies using solid models have been conducted from the 1960s re-entry program of the US [1]. In particular, Helmut G. Heinrich et al. visualized shockwaves, and shockwave vibrations in Mach number 3 [2]. These shockwave vibrations make the flow unstable, and the unstable flow gives model vibrations. They are risks of break.Therefore,Helmut G. Heinrich suggested an improved model.


Mach Number Wind Tunnel Test Model Supersonic Flow Compression Wave 
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  1. 1.
    Charczenko, N.: Wind tunnel investigation of conventional types of parachute canopies in supersonic flow. NASA TMX-991 (1964)Google Scholar
  2. 2.
    Heinrich, H.G.: Aerodynamics of the supersonic guide surface parachute. J. Aircraft 3(2), 105–111 (1966)CrossRefGoogle Scholar
  3. 3.
    Kojyu, H.: Experimental study of aerodynamics about hemisphere model in supersonic flow, Tokyo university, Japan (2006)Google Scholar
  4. 4.
    Takakura, Y., Hiraki, H., Arai, N.: On the Flow Fields around a Concave Body in Supersonic Flow. In: Proceedings of Symposium on Shock Waves in JAPAN, vol. 18-C-1-3, pp. 259–262 (2008)Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • Takafumi Kawamura
    • 1
  • Toshiharu Mizukaki
    • 2
  1. 1.Graduate School of EngineeringTokai UniversityHiratsuka-shiJapan
  2. 2.School of EngineeringTokai UniversityHiratsuka-shiJapan

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