Exploring TBCC engine inlet design for Ma=5

We explore the TBCC (Turbine-Based Combined Cycle) engine inlet design for Mach number equal to 5, highest flight altitude equal to 26 km, inlet total pressure recovery coefficient equal to 0.52055, engine mass flow equal to 331.88 kg·s^-1, and corrected mass flow equal to 150.631 kg·s^-1 In the full paper we explain in some detail the results of our exploration. In this abstract, we just add some pertinent remarks to listing the two topics of explanation. The first topic is: aerodynamic and geometrical design method for the inlet of TBCC engine. Its two subtopics are: the selection of an inlet design point (subtopic 1.1), and the design method and geometry of inlet (subtopic 1.2). In subtopic 1.1, we give the main parameters influencing TBCC engine inlet design and Fig.1 in the full paper showing the flight trajectory of the aircraft carrying the TBCC engine. In subtopic 1.2, we design the geometry of the inlet, its internal contraction ratio being 5.18, lower than that required by the Kantronitz limit. The second topic is: the characteristics of the inlet along flight trajectory and the analysis of ramp angles. Its four subtopics are: control equation, turbulence model, boundary condition and grid discretization (subtopic 2.1), the analysis of the flow field of the inlet on design point (subtopic 2.2), the performance analysis of the inlet along flight trajectory (subtopic 2.3), the analysis of the flow field of the inlet at off-design points (subtopic 2.4). In subtopic 2.3, we adjust the three ramp angles and obtain the flow coefficient and the total pressure recovery coefficient of the inlet under the condition of different Mach numbers, summarized in Figs.7 and 8. The analysis results show preliminarily that the boundary layer and shock interaction induce easier separation regions and that bleed slots improve the separation by eliminating low energy air from the core flow. Computational results show that the performance of the inlet designed by us can satisfy the requirements of the TBCC engine along flight trajectory.