In recent times, high-speed, airbreathing propulsion research has been receiving considerable attention all over the world. This has come about primarily because of renewed interest in the development of reusable launch vehicles employing multimode propulsive systems. The scramjet, a critical subsystem of these composite engines, is still in the developmental stage. A crucial problem in this development is the realization of rapid mixing and heat release with minimum pressure losses inside the supersonic combustor. Recently, a new mixing technique for high-speed flows employing large-scale axial vortices was developed. This involved the use of a lobed supersonic primary nozzle referred to as the petal nozzle. The possibility of applying this novel mixing mechanism to piloted supersonic combustors was examined in this work. Results showed that rapid mixing took place between the hot primary (pilot) stream and the cold secondary airstream when the petal nozzle was used. Piloted secondary (supersonic) combustion of kerosene and acetylene was achieved with satisfactory efficiencies.