Improved design of waverider based on mach line cutting of compression surfaces

An improved forebody design methodology based on the Mach Line Cutting of Compression Surfaces (MLCCS) approach is presented for hypersonic air-breathing waveriders with 2D-planar inlets in this paper, which equips the capacity of taking both precompression flow uniformity and lift-to-drag ratio improvement into account. The MLCCS approach, which verifies that the shapes of compression surfaces beyond the Mach lines would have no effect on the uniformity of the inlet flow, is employed to determine the boundary of the improved region. The improvement of the lift-to-drag ratio is achieved by reducing the lower-surface deflection angles of the improved region. A typical osculating cone waverider is taken as a demonstration to validate the developed improved design methodology. Inviscid and viscous numerical results demonstrate that firstly, the improved waverider could generate a fully attached leading-edge shock wave; secondly, the uniform precompression flows provided by the original and the improved waveriders are identical, while the lift-to-drag ratio could be significantly increased.