Modern configurations of aircraft deal with a high performance design of lifting systems especially oriented to reduction of weight, aerodynamic drag and fuel consumption. The paper shows preliminary results of aerodynamic and structural analyses of a high aspect ratio wing with curved planform, carried out at the Department of Aerospace Engineering of the University of Pisa. In transonic flight condition (high subsonic), for curved planform wing, the wave drag effects are significantly reduced. A numerical comparison, carried out using the FLUENT® code, between curved and traditional swept wing, both designed with the same supercritical airfoil, shows a drag coefficient reduction of 4% and more for asymptotic Mach numbers greater than 0.85. The B787 aircraft’s wing planform has been assumed as reference geometry to carry out the numerical analyses. The curved planform configuration also improves the aeroelastic behaviour of the wing: some preliminary results obtained using the NASTRAN® code are summarized in the paper.
HIGH ASPECT RATIO WING WITH CURVED PLANFORM: CFD AND FE ANALYSES
CHIARELLI, MARIO ROSARIO;
2010-01-01
Abstract
Modern configurations of aircraft deal with a high performance design of lifting systems especially oriented to reduction of weight, aerodynamic drag and fuel consumption. The paper shows preliminary results of aerodynamic and structural analyses of a high aspect ratio wing with curved planform, carried out at the Department of Aerospace Engineering of the University of Pisa. In transonic flight condition (high subsonic), for curved planform wing, the wave drag effects are significantly reduced. A numerical comparison, carried out using the FLUENT® code, between curved and traditional swept wing, both designed with the same supercritical airfoil, shows a drag coefficient reduction of 4% and more for asymptotic Mach numbers greater than 0.85. The B787 aircraft’s wing planform has been assumed as reference geometry to carry out the numerical analyses. The curved planform configuration also improves the aeroelastic behaviour of the wing: some preliminary results obtained using the NASTRAN® code are summarized in the paper.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
