ECLIPPS: 2. CFD Prediction of the Performance Degradation Due to Ice

Dezitter, Fabien; Caminade, Francois; Catris, Stéphane; Guffond, Didier; Montreuil, Emmanuel; Aupoix, B.; Houdeville, R.; Arnal, D.

doi:10.2514/6.2009-3970

Cited by 3 publications

(2 citation statements)

References 16 publications

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“…The computed pressure coefficients are compared to both experimental and numerical results (AG-32 2003). It is to be noticed that none of the CFD code pressure coefficients available in the literature (Dezitter et al 2009) agree with the experiments in the separation regions. The figure 17 shows the C p computed on the three meshes with SU2 and without roughness model.…”

Section: Iced Naca 0012mentioning

confidence: 87%

“…This model represents an outer wing section of a transport aircraft. This test case corresponds to case C1 in the AG-32 final report, documented in AG-32 ( 2003), Dezitter et al (2009) and Tagawa et al (2018). The leading edge glaze ice shape was calculated by Fokker, for which the reference icing conditions were at an angle of attack of 4 • , an ambient pressure of 0.57 bar, a speed of 101.2 m/s, an outside temperature of -14.7 • C, a water concentration of 1.96 g/m 3 , a median volumetric droplet diameter of 20 µm, an accretion time of 148 s, and a chord of 1.257 m. The model used for the aerodynamic measurement model as a chord of 0.6759 m, and the ice shape has an average grain size of h s = 0.6 mm (Tagawa et al 2018).…”

Section: Model 5-6mentioning

confidence: 95%

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Comparison of turbulent Prandtl number correction models for the Stanton evaluation over rough surfaces

Morency

Beaugendre

2020

International Journal of Computational Fluid Dynamics

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In-flight ice accretion code predictions depend on heat loss over rough surfaces. The equivalent sand grain roughness models the friction coefficient, but an additional model is needed for heat transfer predictions. In this paper, a two parameters model based on a turbulent Prandtl number correction is derived from the sublayer Stanton-based model. For flow over rough surfaces, the new model predictions will be compared to a three parameters model from the literature. First, the models are coupled with the Spalart-Allmaras turbulence model to predict heat transfers over rough surfaces. Thereafter, the two models are implemented in the open source software, SU2, and then verified and validated for flow over rough flat plates. Lastly, the predictions of the two models are shown to be similar for ice accretion roughness on flat plates, airfoils and a wing. Model discrepancies are always within the experimental 15% error margin.

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Section: Iced Naca 0012mentioning

confidence: 87%