Abstract
A subscale scramjet engine was designed on the basis of the component study results. Both a heat-sink model and a water-cooled model were fabricated. The heat-sink engine has been tested in a free-jet engine test facility simulating flight conditions of Mach 4 at 20 km altitude and Mach 6 at 25 km. In the Mach 4 test, successful ignition of the main fuel was achieved by the plasma torch igniters with pilot fuel injection. However, in the Mach 6 test, only partial ignition of the fuel was achieved with the same configuration. Wall pressure and temperature distributions as well as forces were measured.
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© 1997 Springer Science+Business Media Dordrecht
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Masuya, G., Chinzei, N., Miki, Y. (1997). Scramjet Engine Tests at Mach 4 and 6. In: Champion, M., Deshaies, B. (eds) IUTAM Symposium on Combustion in Supersonic Flows. Fluid Mechanics and Its Applications, vol 39. Springer, Dordrecht. https://doi.org/10.1007/978-94-011-5432-1_12
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DOI: https://doi.org/10.1007/978-94-011-5432-1_12
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