The development of a high-order accurate incompressible Navier-Stokes solver based on the vorticity-velocity formulation for orthogonal curvilinear grids is presented and discussed. The solver is written in Fortran 90, and it is parallelized using a hybrid MPI-OpenMP strategy. State-of-the-art numerical algorithms have been incorporated that are especially designed for direct numerical simulations of transitional and turbulent flows. Towards this end, sixorder split and central compact-difference discretizations are employed for the computation of spatial derivatives in the streamwise and wall-normal directions together with a pseudo spectral treatment of the spanwise direction. The governing equations are integrated in time using a strong stability preserving form of the explicit four-stage Runge–Kutta scheme. A highly efficient, high-order accurate Poisson solver, based on a combination of the fourth-order compact finite-difference scheme and a multiscale multigrid method, was developed for solving the (steady) convection-diffusion type equation with variable coefficients for the velocity Poisson equations that result from the vorticity-velocity formulation of the Navier-Stokes equations. An efficient approach is employed that guarantees the divergence-free condition for the velocity and vorticity fields. In addition, a new hybrid approach for generating structured grids with high orthogonality and smoothness, while achieving a desired wall-normal distance required for turbulent boundary layers, is implemented. In this strategy, orthogonal grids are generated first by solving a set of Poisson equations, then the grids are modified by using the orthogonality constraint and a general form of Cauchy–Riemann relations for conformal mapping. In the present paper, results obtained from the new Navier-Stokes solver are compared with benchmark solutions for the flow past a circular cylinder. Furthermore, the new solver was employed for a three-dimensional direct numerical simulation of the uncontrolled flow for a modified NACA 643-618 airfoil at a chord Reynolds number of '4 = 200: And zero angle of attack.