The model ( scale 1:5 ) of Anuloid aircraft was tested in a large wind tunnel of Mechanical and Aerospace Department-Politecnico di Torino. The evaluation of the aerodynamic performances were performed using a 6 component external balance for the force and moments measurements. Also pressure distributions around the model were assessed. The investigation was conducted varying the incidence for two Reynolds number ( Re=6.8105 and Re=2.1106). In addition flow visualizations were performed using tufts attached to half body on both sides. The model for the wind tunnel investigations has been manufactured by the cooperative work executed by PoliTo e VZLU. The fan flow was not reproduced due the very complex solution for the mounting that would introduce a huge flows interference making the interpretation of the results really questionable. Only the body aerodynamic was as a consequence tested. For negative incidences corresponding to the normal flight conditions the lift is approximately equal to zero while considerable drag takes place. For positive incidences the lift and drag curves change trend as expected showing monotonic increasing of the forces coefficient as the incidence increases. The pitching moment coefficient is always negative and increases nearly in a linear way with the incidence especially for the lower Reynolds number. Reynolds effect is present in particular in the positive range of incidences. The pressure distributions reported in terms of colored maps evidence very 3D complex flow fields changing according with the incidence. Flow visualizations highlighted three-dimensional vortical flows generated especially around the most external annuli on the lower. On the rear part of the upper surface a region of separated and highly unsteady flow is present.

Wind Tunnel Investigation on 1:5 Anuloid Model / Iuso, Gaetano; Sardu, Costantino; C., Sedda. - EU Project ANULOID:(2015).

Wind Tunnel Investigation on 1:5 Anuloid Model

IUSO, Gaetano;SARDU, COSTANTINO;
2015

Abstract

The model ( scale 1:5 ) of Anuloid aircraft was tested in a large wind tunnel of Mechanical and Aerospace Department-Politecnico di Torino. The evaluation of the aerodynamic performances were performed using a 6 component external balance for the force and moments measurements. Also pressure distributions around the model were assessed. The investigation was conducted varying the incidence for two Reynolds number ( Re=6.8105 and Re=2.1106). In addition flow visualizations were performed using tufts attached to half body on both sides. The model for the wind tunnel investigations has been manufactured by the cooperative work executed by PoliTo e VZLU. The fan flow was not reproduced due the very complex solution for the mounting that would introduce a huge flows interference making the interpretation of the results really questionable. Only the body aerodynamic was as a consequence tested. For negative incidences corresponding to the normal flight conditions the lift is approximately equal to zero while considerable drag takes place. For positive incidences the lift and drag curves change trend as expected showing monotonic increasing of the forces coefficient as the incidence increases. The pitching moment coefficient is always negative and increases nearly in a linear way with the incidence especially for the lower Reynolds number. Reynolds effect is present in particular in the positive range of incidences. The pressure distributions reported in terms of colored maps evidence very 3D complex flow fields changing according with the incidence. Flow visualizations highlighted three-dimensional vortical flows generated especially around the most external annuli on the lower. On the rear part of the upper surface a region of separated and highly unsteady flow is present.
2015
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11583/2614155
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