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Performance Analysis of a Scramjet Combustor with Cavity for Mach Numbers 3.0, 3.25 and 3.50 with Hydrogen as a Fuel

Crossref DOI link: https://doi.org/10.1007/978-981-15-7711-6_91

Published Online: 2021-01-11

Published Print: 2021

Update policy: https://doi.org/10.1007/springer_crossmark_policy

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