Notice of RetractionNumerical study of aerodynamic performance of a aircraft swept wing with leading-edge ice accretions

Notice of Retraction

After careful and considered review of the content of this paper by a duly constituted expert committee, this paper has been found to be in violation of IEEE´s Publication Principles.

We hereby retract the content of this paper. Reasonable effort should be made to remove all past references to this paper.

The presenting author of this paper has the option to appeal this decision by contacting TPII@ieee.org.

This paper deals with the computational studies carried out on the aircraft swept wing with and without leading edge ice accretions at subsonic Mach number conditions. The aerodynamic performance penalty of lift and drag coefficients were evaluated. The computation were carried out at Mach number 0.4758 with the Reynolds number 5.61×10⁶ conditions to obtain the flow field around the swept wing with and without 5 minutes rime and 2 minutes glaze ice accretions. The pressure distribution over the aircraft swept wing with each ice accretion on the angles of attack 0, 2, 4 and 6 degrees have also been investigated. This computational study is based on the Fluent-UNS code using the one equation Spalart-Allmaras(S-A) turbulence model and second order upwind differencing. In this paper, we only the steady-state solution were sought. The computed results show that the aerodynamic performance of aircraft swept wing is more sensitive to the glaze ice accretion such as leading-edge horn than to the local variation of surface roughness distribution. The results show that the 3-D CFD computation can accurately predict the lift and drag coefficients for the swept wing with ice accretions.