Under the frame of finite volume methodology

MLP (multi-dimensional limiting process) scheme was further modified by introducing a shock-detect function to decrease the numerical dissipation in smooth regions

then supersonic flow over facing step

unsteady flow over an airfoil with ice accretion

hypersonic flow over double wedge configuration flow and subsonic flow over DLR F6-WB complex configuration were investigated by utilizing MLP high order reconstruction scheme and HLL-HLLC (Harten-Lax-van Leer with contact) approximate Riemann solver to validate the performances of proposed schemes in sophisticated compressible flow simulations. The research illustrates that: MLP can keep strict monotone flow characteristics even in the complex high-dimension fluid simulations consisting of strong oblique shock waves not aligned with grids; it has the similar computational efficiency compared with traditional MUSCL (monotone upstream-centered schemes for conservation laws) scheme and can achieve fifth or even higher order reconstruction; it features low numerical dissipation so that more accurate shock position can be captured

therefore MLP scheme is promising for aerospace engineering applications.