Young Jin KIM, Hyoung Jin LEE
DOI Number: XXX-YYY-ZZZ
Conference Number: HiSST-0041
Scramjet engines used for efficient flight in supersonic and hypersonic areas have the disadvantage of not generating thrust at subsonic and stationary conditions. Therefore, ramjet or scramjet engines are not used alone but in complex cycles such as TBCC(Turbine Based Combined Cycle) and RBCC (Rocket Based Combined Cycle) combined with turbine or rocket engines. In such an integrated propulsion system, a configuration design for a variable inlet is required since operation is essential in a wide range of Mach numbers. In this study, the required mass flow conditions of the TBCC aircraft were derived, and the shape design and detailed design procedures of the variable inlet satisfying them were presented. The maximum operating Mach number of the variable inlet was set to 7, and the shape of the variable suction port was designed using variable lamps and cowls to satisfy the required flow rate conditions for each Mach number. Boundary layer correction and computational analysis were performed on the designed shape. As a result of two-dimensional numerical simulation, it was confirmed that the mass flow rate flowing into the inlet satisfies the requirements. After that, a wind tunnel test was performed by creating a reduction model for the variable inlet for Mach 2 and 7. The supersonic wind tunnel was used in Mach 2, and the hypersonic shock wave tunnel was used in Mach 7. In each test, the inlet performance analysis was performed through back pressure control and verification of the designed inlet shape. As a result of the wind tunnel test, it was verified that the shape of the inlet in each Mach number was carried out properly, and the starting characteristics according to the back pressure were confirmed.