Evolution of Flow Instability in Channel Imposed with Wall Blowing
- Paper number
IAC-09.C4.P.8
- Author
Prof. Changjin Lee, Konkuk University, Korea, Korea, Republic of
- Year
2009
- Abstract
This paper is devoted to the LES analysis for the oscillating intrinsic flow in the presence of acoustic excitations. The flow condition in the hybrid rocket combustion is very similar to the flow in solid rocket combustion in that the interaction of axial flow with wall blowing flow dominates in the chamber. And the interaction may produce periodic oscillations inside of turbulent boundary layer after it flows down through laminar and transient flow regime. Since the turbulent flow of oxidizer is prevalent from the inlet of the hybrid rocket chamber, it is very difficult to predict the modification of periodic oscillating flow when acoustic excitations are imposed. In this study, LES technique is used to investigate the response of the oscillating flow confined to the vicinity of propellant surface when the acoustic excitation is applied to the flow field.
- Abstract document
- Manuscript document
(absent)