The paper shows preliminary results of aeroelastic analyses of two half-wing models, having curved and swept planform, carried out at the Aerospace Unit of the Department of Civil and Industrial Engineering of Pisa University. For a wing with a curved planform, as demonstrated in previous papers regarding rigid models of wings, the wave drag effects are strongly reduced in the transonic flight conditions. In the paper some results obtained by using Star-CCM+® 6.04.14 and Abaqus® 6.11 in “co-simulation” are summarized: for this reason the present numerical comparison, between a curved wing and a swept wing, includes the effects of structure’s deformability (the wings have the same aspect ratio). The beneficial effects of the planform shape on drag polar curves are confirmed. Moreover the curved planform configuration improves the wing’s aeroelastic behavior: for a fixed value of CL the reaction moments and stress values at the root of the curved wing are reduced by about 5%÷8% with respect the data obtained for the swept wing at the same flight conditions. Finally, preliminary numerical analyses carried out at high angles of attack show that, as expected, the centers of pressure of the wings move forward with percentage variation of their longitudinal positions that are quite similar. These results indicate that the curved planform shape does not change in a drastic fashion the performances of a wing when the stall condition are reached.

Fluid-Structure Interaction Analyses of Wings with Curved Planform: Preliminary Aeroelastic Results

CHIARELLI, MARIO ROSARIO;LOMBARDI, GIOVANNI
2013

Abstract

The paper shows preliminary results of aeroelastic analyses of two half-wing models, having curved and swept planform, carried out at the Aerospace Unit of the Department of Civil and Industrial Engineering of Pisa University. For a wing with a curved planform, as demonstrated in previous papers regarding rigid models of wings, the wave drag effects are strongly reduced in the transonic flight conditions. In the paper some results obtained by using Star-CCM+® 6.04.14 and Abaqus® 6.11 in “co-simulation” are summarized: for this reason the present numerical comparison, between a curved wing and a swept wing, includes the effects of structure’s deformability (the wings have the same aspect ratio). The beneficial effects of the planform shape on drag polar curves are confirmed. Moreover the curved planform configuration improves the wing’s aeroelastic behavior: for a fixed value of CL the reaction moments and stress values at the root of the curved wing are reduced by about 5%÷8% with respect the data obtained for the swept wing at the same flight conditions. Finally, preliminary numerical analyses carried out at high angles of attack show that, as expected, the centers of pressure of the wings move forward with percentage variation of their longitudinal positions that are quite similar. These results indicate that the curved planform shape does not change in a drastic fashion the performances of a wing when the stall condition are reached.
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Utilizza questo identificativo per citare o creare un link a questo documento: http://hdl.handle.net/11568/262735
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