CWI's research has a theme-oriented structure and is grouped into four clusters. Listed below are the names of the clusters and in parentheses their acronyms. ABSTRACT This paper describes the application of a composite overset-grid technique to flow computations around a two-dimensional bi-plane. The flow is described by the steady, 2D, compressible Euler equations of gas dynamics. The discret...

Direct numerical simulation results of aeolian tones generated by a two-dimensional obstacle (circular cylinder, square cylinder, NACA0012 airfoil) in a uniform flow are presented and the generation and propagation mechanisms of the sound are discussed. The unsteady compressible Navier-Stokes equations are solved by a highly-accurate finite difference scheme over the entire region from near to ...

Flow transitions are an important fluid-dynamic phenomena for many reasons, including the direct effect on aerodynamic forces acting body. In present study, two-dimensional (2-D) and three-dimensional (3-D) wake of a NACA0012 airfoil studied angles attack in range $0^\circ \leq \alpha 20^\circ$ Reynolds numbers $500 {\textit {Re}} 5000$ . The study uses water-channel experiments 2-D 3-D numeric...

A high order staggered-grid Chebyshev multidomain method is used to compute the Euler gas-dynamics equations on unstructured quadrilateral meshes. New results show that the method reduces to the first order upwind scheme when zeroth order polynomial approximations are used, and that by a simple reconstruction procedure the standard Chebyshev collocation method can be recovered. Local time-stepp...

A jet with a width of 2.5% the chord length is placed on a NACA0012 airfoil’s upper surface simulating the blowing and suction control under Re = 5 × 105 and angle-of-attack 18-deg conditions. Nearly 300 numerical simulations are conducted over a range of parameters (jet location, amplitude, and angle). The physical mechanisms that govern suction and blowing flow control are determined and anal...

The aerodynamics of an aerofoil with surface heating was numerically studied the objective to build effective anti-icing strategy and balance performance energy consumption. NACA0012, RAE2822 ONERA M6 aerofoils were adopted as test cases simulations performed in subsonic flight condition commercial passenger aircraft. In first session, numerical scheme firstly validated experimental data. A par...