MACH-6 TESTING OF A SCRAMJET ENGINE MODEL

Testing of a subscale scramjet research engine model was carried out i n the Mach 6 Ramjet Engine Test Facility of the National Aerospace Lab oratory, Kakuda Research Center. The engine had a sidewall compression -type inlet. The fuel was hydrogen. With the attachment of a short str ut on the top wall, intensive combustion with high-combustion efficien cy was attained, and the engine-produced thrust canceled the drag. The flame was held in the low-velocity region around the step, even after the ignitors had been turned off. When the fuel flow rate was small, there was a different combustion mode with weak combustion and little thrust. The unstart condition seemed to begin around the cowl. Tangent ial injection of fuel inhibited intensive combustion.