This work presents CFD results obtained with an efficient, high-order, finite-volume scheme. The formulation is
based on the variable extrapolation MUSCL-scheme, and high-order spatial accuracy is achieved using correction
terms obtained through successive differentiation. The scheme is modified to cope with physical and multiblock
mesh interfaces, so stability, conservativeness, and high-order accuracy are guaranteed. Results with the proposed
scheme for steady flows, showed better wake and higher resolution of vortical structures compared with
the standard MUSCL, even when coarser meshes were employed. The method was also demonstrated for unsteady
flows using overset and moving grids for the UH-60A rotor in forward flight and the ERICA tiltrotor in aeroplane
mode. The present method adds CPU and memory overheads of 47% and 23%, respectively, in performing
multi-dimensional problems for routine computations
