Summary
The combustion performance of a two-dimensional scramjet engine model with inlet and tangential injection was experimentally investigated in the HIEST free-piston shock tunnel. Experiments were performed at a free-stream Mach number of 7, a stagnation enthalpy of 6 MJ/kg and a stagnation pressure of 30 MPa. The use of inlet injection or combined inlet and tangential injection resulted in reduced ignition times and improved combustion pressure levels when compared to tangential injection. In addition, a lower injection angle or downstream injection position for inlet injection has the potential to minimise inlet losses without significantly affecting engine pressure levels.
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© 2009 Springer-Verlag Berlin Heidelberg
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Rowan, S., Komuro, T., Sato, K., Itoh, K. (2009). Combustion performance of a scramjet engine with inlet injection. In: Hannemann, K., Seiler, F. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-85168-4_88
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DOI: https://doi.org/10.1007/978-3-540-85168-4_88
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-85167-7
Online ISBN: 978-3-540-85168-4
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