Abstract:
This work presents the development and implementation of an efficient, compact high-order finite-volume scheme in the HMB CFD solver. This formulation is based on the variable extrapolation MUSCL-scheme, where high-order spatial accuracy (up to 4th-order) is achieved using high-order correction terms through a successive differentiation. The scheme has also been modified to cope with physical and multiblock mesh interfaces, so stability, conservativeness, and high-order accuracy are guaranteed. A wide variety of results for the underlying method are presented, including two-and three-dimensional test cases. The convection of an isentropic vortex, and the aerodynamic interaction between a vortex and a NACA-0012 aerofoil (blade vortex interaction problem BVI) are first studied, demonstrating the high level of accuracy of the new formulation. Theoretical and numerical analyses of the truncation error are also included. The three-dimensional steady flows around the 7AD, S-76, and XV-15 blades are also computed. Results with the proposed scheme, showed better wake and higher resolution of the vortical structures compared with the standard MUSCL solution, even though a coarse mesh was employed. The method was also demonstrated to three-dimensional unsteady flows using overset and moving grid computations for the UH-60A rotor in forward flight. The effect that the present method adds a CPU overhead of 40% in performing multi-dimensional problems encourages its use for routine computations.