Methodical Aspects of Investigation of Kerosene Ignition and Combustion in Scramjet Model

Introduction The latest studies of the overall characteristics of hypersonic flying vehicles with airbreathing engines have shown that these vehicles are fairly promising. Some additional problems arise, however, that are related to the definition of the general shape of the aircraft, the choice of propulsion type and operation regimes, the engine size and position on the aircraft body. There have been studies on hydrocarbon-fuelled vehicle concept in a range of Mach numbers. It is assumed that the upper bounds of using hydrocarbon fuels lie between Mach numbers 6-8 [1]. Many investigations of scramjets with a hydrogen fuel on models in wind tunnels of are known [2]. But only few works are known, which concerned the study of hydrocarbon fuel combustion and especially combustion of liquid kerosene. Therefore, the investigation of liquid fuel combustion is very important. It is necessary to evaluate the possibility of full engine model tests in a hot-shot wind tunnel under flight conditions. The main aims of researches were: • to obtain characteristics of the full engine (and its elements) in ramjet and scramjet regimes; • to compare these characteristics with the calculation results obtained with CFD and engineering methods; • to prove the possibility of scramjet tests in a hot-shot wind tunnel; • to study the ignition and combustion (injection and stabilisation) of a liquid hydrocarbon fuel in scramjet mode; • to obtain positive effective thrust.