Delayed Detached Eddy Simulations (DDES) of separating-reattaching flows on the suction side of an ice-contaminated airfoil were conducted. A single-section straight-wing NACA23012 airfoil with leading-edge ice was studied. The geometry represents a realistic glaze horn-ice contamination obtained during the icing test campaigns described in [1], which has aerodynamic data for comparison. The three-dimensional transient flow behavior was simulated using the open-source flow solver OVERFLOW, version 2.2l [2] developed by NASA Langley Research Center. Configurations at three angles of attack that exhibit unsteady flow behavior starting with the bursting angle were examined at Mach number of 0.18 and Reynolds number of 1.8x106. As the stall angle was approached the aerodynamic performance parameters displayed large-scale unsteadiness where periods of attached and separated flows were observed. The time-averaged results show good agreement with the aerodynamic test data. The calculated Strouhal number for the self-sustained low-frequency oscillations is consistent with the previous experimental research.
Separating-Reattaching Flows Over an Iced Airfoil
Sae Technical Papers
International Conference on Icing of Aircraft, Engines, and Structures ; 2019
2019-06-10
Aufsatz (Konferenz)
Englisch
Separating-Reattaching Flows Over an Iced Airfoil
British Library Conference Proceedings | 2019
|Elsevier | 2005
|Online Contents | 2005
|Iced-Airfoil and Wing Aerodynamics
British Library Conference Proceedings | 2003
|