RANS and LES modeling are applied to the geometrically complex problem of glaze ice accretion on fixed-wing and rotorcraft airfoils. The shortcomings of transport based RANS turbulence models for these systems is demonstrated using three experimental data sets. The roles of meshing topology, turbulence model choice, and 2D assumptions are quantified. Despite best practice implementation of RANS modeling, results show that these methods consistently under-predict stall onset and high-α lift. The reason for this poor performance is parametrically explored. It is shown that the smaller-scale (O[102 μm]) and larger scale (i.e., bluff "horns") geometric features of the ice shapes that give rise to a rich inertial 3D unsteady flow, at and aft of the leading edge, are primarily responsible, as these are largely inaccessible to RANS. Implicit LES results are presented that demonstrate improvement in predicted aerodynamic performance.
|Original language||English (US)|
|Journal||Transactions of Japanese Society for Medical and Biological Engineering|
|State||Published - 2013|
|Event||35th Annual International Conference of IEEE Engineering in Medicine and Biology Society, EMBC 2013 in conjunction with 52nd Annual Conference of Japanese Society for Medical and Biological Engineering, JSMBE - Osaka, Japan|
Duration: Jul 3 2013 → Jul 7 2013
All Science Journal Classification (ASJC) codes
- Biomedical Engineering