A transition prediction module for 3D compressible flows was developed by the authors in order to include the prediction of the laminar-turbulent transition in hydrodynamics computational codes; particularly the module was integrated in the general-purpose gas-dynamic package ANSYS Fluent. The subsonic air flow about a swept wing model with the sweep angle of 45° and the chord of 700 mm was computed (U_∞=10:36m/s) at angles of attack α=+3°; the positions of the laminar-turbulent transition were detected for different mechanisms of instability. The mechanism of boundary layer instability to the Tollmien-Schlichting waves dominates at the angle of attack +3°, the line of the laminar-turbulent transition being not parallel to the wing leading edge.
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