Analysis on flow around a sphere at high mach number, low Reynolds number and adiabatic condition for high accuracy analysis of gas particle flows (original) (raw)

Abstract

The exhaust gas from rocket motors generates severe acoustic waves. The acoustic waves reflected from the ground and launch facility is cause of vibration of the payload in the fairing. Therefore, prediction and reduction of acoustic level at the lift-off is quite important. Traditionally, acoustic level has been predicted by an empirical method, NASA SP-8072 [1] or subscale tests [2] . In recent, prediction of acoustic level by CFD is required, because an empirical methods does not have enough accuracy. The alumina particles released from solid rocket motors might attenuate acoustic wave, but the mechanism is not well known. Therefore, a new model for prediction of drag force at the highMach-number and low-Reynolds-number condition is necessary, in order to perform high accuracy prediction on acoustic wave generated by exhaust gas from solid rocket motors. In this study, the high-Mach-number and low-Reynolds-number flow analysis of the around a sphere by direct numerical simulation...

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References (3)

  1. Eldred,K.M., "Acoustic Loads Generated by the Propulsion System", NASA SP-8072, 1971.
  2. Ishii T., Tsutsumi S., Ui K., Tokudome S., Ishii Y., Wada K. and Nakamura S., "Acoustic Measurement of 1:42 Scale Booster and Launch Pad", Proceedings of Meetings on Acoustics, Volume 18, 2014
  3. Johnson T. A. and Patel V. C., "Flow past a sphere up to a Reynolds number of 300", Journal of Fluid Mechanics, Volume 378, January 1999, pp. 19-70, 1999.

Last updatedNovember 28, 2024