Li RUI, Xu JINGLEI, Zhang KUNYUAN

DOI Number: N/A

Conference number: HiSST-2025-352

This study numerically investigates the performance of a non-premixed continuous detonation ramjet fueled by ethylene. The design point is set to a flight Mach number of five at the flight height of 20 km, and the fuel is pumped into the cavity-based combustor at a total pressure of 1 MPa and a total temperature of 300 K. After the ignition, the working frequency is stabilized at 5787 Hz, and the model reaches a mass flow rate of 0.52 kg·s-1. In the entire operating process, the reverse shock wave occupies one-third of the axial length of the isolator, and the strength of the trailing shock wave weakens along the flow path. At the combustor exit, RMSDθ and Mach number are separately equal to 6.57°and 1.04, indicating that the flow fluctuations are moderate and the nozzle converging section is unnecessary. These features imply that the design of the compression system and the exhaust system for this engine outline can still follow the methods in steady flows to some extent. In addition, the increase in the total temperature is 1503 K, demonstrating the superiority of detonation in the energy addition to the high-speed mainstream.

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In Categories: 1.Events, 1.HiSST 2025, High-Speed Aerodynamics and Aerothermodynamics with application to hypersonic regimes
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