Further downstream on the airfoil surface the flow becomes again subsonic by means of a nearly normal shock wave. The Mach number far away of the airfoil Ma inf 1) on one or both sides of the airfoil depending on its shape and incidence angle. Transonic means that part of the flow around the airfoil is subsonic and parts are supersonic. Apply the found setup to the moving airfoil.Study of the influence of the angle of attach and Mach number.Study of the discretization of the convective schemes.The tutorial is divided into five different smaller tutorial to make things easier for the reader. This keeps the complexity of the flow phenomena to a minimum. At low angles of attack the flow remains attached or forms a closed recirculation bubble after the large pressure gradient induced by a shock wave without a massive flow separation. The scope of this tutorial is to evaluate the capability of the solver rhoPimpleFoam to simulate a periodically pitching airfoil in a transonic flow at low angles of attack. Transonic flow around a periodically pitching NACA0012 airfoil 1.6 Study of the influence of the angle of attach and Mach number.1.4 Study of the discretization of the convective schemes.
1 Transonic flow around a periodically pitching NACA0012 airfoil.
0 kommentar(er)
