| Abstract: | With hypersonic vehicle design becoming a focus for reusability, high flight rates, and benefit to civilian transportation systems, understanding propulsion and airframe integration is key. It is of interest to know how changing the mission requirements of a vehicle has an impact on the geometry of the inlet. By understanding the flow path that is needed for an inlet to operate at the needed pressure recovery and match the needed conditions of the engine, a relationship between the airframe geometry and propulsion system can be made. As a result, several vehicle configurations have been selected that are designed for high-speed flight and will provide cases for understanding the design of their intakes. This development has started with the XB-70 and Concorde and major characteristics of their inlet is discussed. From these findings, we developed a method that provides the design of a 2D mix-compression inlet and outputs the dimensions of length, heights, Mach number along inlet, deflection angles, and shock angles. The method was then extended by taking the geometry of the XB-70, Concorde, and Tu-144 and modeling the dimensions of the inlet. The effects of the inlet on the airframe will be investigated. |