Abstract
AbstractTurbulent flows around aerofoils and wings are simulated by solving the two‐and three‐dimensional Navier‐Stokes equations in quadrilaterals and hexahedrons, respectively. Turbulent flow is described by an algebraic eddy viscosity model. Boundary‐conforming O‐and O‐Otype meshes are generated by the transfinite interpolation method. The finite‐volume technique is employed for spatial discretization using two cells in each computational co‐ordinate direction more than the conventional approach to evaluate the viscous fluxes. An explicit three‐stage Runge–Kutta scheme is used for time integration. The method is applied to compute turbulent transonic flow over the NACA 0012 aerofoil and the ONERA M6 wing. The results are compared with experimental and computational data.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
