Abstract
In this study, quasi-1D analysis with chemical equilibrium was applied at a sub-scale rocket-based combined cycle (RBCC) engine for a hypersonic flight test using a sounding rocket. A mission profile of the engine was designed in a previous study, and its off-design performance was examined in test-mission research for the flight test. The operational conditions are Mach 3 to 7 at altitudes of 10 to 30 km. A bleed duct and a pre-burner are applied in the engine. The analysis method was validated by comparison with HyShot II flight test data to ensure reliability. The thrust and the specific impulse at each design point are 595 N and 646 s in scramjet mode, while they are 9.07 kN and 1,543 s in ramjet mode.
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