Computation of Flow over a High-Performance Parafoil Canopy

摘要: The incompressible Navier-Stokes equations together with the one equation Spalart-Allmaras turbulence model were solved using a finite volume flow solver to examine flowfield and forces on central cross section of high-performance parafoil canopy. surfaces assumed be impermeable, rigid, smooth. consists vortex inside cell opening, which effectively closes off opening diverts around leading edge. about experiences rather bluff edge, in contrast smooth baseline airfoil. A separation bubble exists lip lower surface. lift coefficient increases linearly angle attack up 8.5 degrees lift-curve slope is 8% smaller than same for has major effect drag before stall; at least twice airfoil drag. minimum occurs over angle-of-attack range 2.5-7 degrees.