Visualization of Combustion Within a Hybrid Rocket Motor
نویسنده
چکیده
A visualization facility has been developed at Stanford University in order to study flow in a turbulent combustion boundary layer. The motivation for the facility arises from recent studies of fast burning fuels for hybrid rocket propulsion where droplet lift-off from the melting fuel surface is the dominant mass transfer mechanism. The facility, shown in Figure 1, has been used to image the combustion of various fuels with gaseous oxygen. Five classical fuels have been tested, specifically Hydroxyl-Terminated PolyButadiene (HTPB) with 0.5% by mass carbon black, HTPB without carbon black, High Density PolyEtheylene (HDPE), Acrylonitrile Butadiene Styrene (ABS), and PolyMethyl MethAcrylate (PMMA) as well as a liquefying high regression rate fuel, specifically neat paraffin with 0.5% by mass of black dye, referred to as Blackened Paraffin (BP).
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