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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