Design Procedure of a Variable Rectangular Inlet for TBCC Engine Considering Mass Flow Requirements

초록

Ramjet or scramjet engines, high-speed air-breathing propulsion systems, can only be operated in supersonic and hypersonic regions. Therefore, ramjet or scramjet engines are not used alone but in the form of a combined cycle, such as the turbine-based combined cycle (TBCC) and rocket-based combined cycle combined with turbine or rocket engines. Configuration design of the variable inlet is necessary because operation in a wide range of Mach numbers is essential in these integrated propulsion systems. This study presented a detailed design procedure for a 2D variable inlet for TBCC engines, taking into account the changing mass flow rate conditions based on mission trajectories. The design procedure was validated by deriving the mass flow requirements for the aircraft conceptually and designing the variable inlet geometry accordingly. The designed variable inlet geometry underwent boundary layer correction, accounting for viscous effects. Subsequently, the performance of the designed variable inlet was analyzed through numerical simulations. A comparison of the outlet performance with inlets operating in a similar range and design conditions confirmed the significant improvement achieved by the designed variable inlet.

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