The effects of the planform on the aerodynamic drag have been numerically investigated and compared, in the high subsonic regime and low angles of attack, for three wing models: a straight wing, a forward swept wing and a forward curved planform wing. The semispan (0.7 m), the aspect ratio (5.7), the taper ratio (0.4) and wing sections (NACA 0012) are the same. For the straight and swept wing models some experimental results are available in the literature. CFD analyses have been executed using three structured grids: the code STAR–CCM+® has been used in the research. Drag polar curves, at Mach number 0.7, confirm that the planform of a wing strongly influences the pressure distribution and the drag coefficient: with a lift coefficient ranging through –0.25 and 0.25 the curved planform wing develops the minimum of the drag coefficient thanks to reduction of both pressure drag and shock wave effects.
A Straight Wing and a Forward Swept Wing Compared with a Curved Planform Wing in the Transonic Regime
CHIARELLI, MARIO ROSARIO;LOMBARDI, GIOVANNI;
2011-01-01
Abstract
The effects of the planform on the aerodynamic drag have been numerically investigated and compared, in the high subsonic regime and low angles of attack, for three wing models: a straight wing, a forward swept wing and a forward curved planform wing. The semispan (0.7 m), the aspect ratio (5.7), the taper ratio (0.4) and wing sections (NACA 0012) are the same. For the straight and swept wing models some experimental results are available in the literature. CFD analyses have been executed using three structured grids: the code STAR–CCM+® has been used in the research. Drag polar curves, at Mach number 0.7, confirm that the planform of a wing strongly influences the pressure distribution and the drag coefficient: with a lift coefficient ranging through –0.25 and 0.25 the curved planform wing develops the minimum of the drag coefficient thanks to reduction of both pressure drag and shock wave effects.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
