NASA NTRS · 19670000455
A method of determining combustion gas flow
Abstract
Zirconium oxide coating enables the determination of hot gas flow patterns on liquid rocket injector face and baffle surfaces to indicate modifications that will increase performance and improve combustion stability. The coating withstands combustion temperatures and due to the coarse surface and coloring of the coating, shows the hot gas patterns.
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Bon Tempi, P. J.. 1968-01-01. A method of determining combustion gas flow. https://ntrs.nasa.gov/citations/19670000455
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