Advanced airfoil design for general aviation propellers

Taverna, Frank

doi:10.2514/6.1983-1791

Cited by 5 publications

(1 citation statement)

References 8 publications

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“…Yet, to the authors' knowledge, studies on this particular profile are limited to the aerodynamic performance [11], [12], the data collected in [1], the validation results in [2], which are more than three decades old, and the roughness-induced transition study in the transonic regime for a symmetric NACA 16-series airfoil in [24]. In the study of the flow around immersed bodies such as airfoils, the knowledge of the actual laminar/turbulent/separated state of the boundary layer is of high importance given its implications on the performance and behavior of the body under scrutiny [13]- [15].…”

Section: Introductionmentioning

confidence: 99%

Laminar-Turbulent Transition on a Cambered NACA 16-009 Airfoil at Low Speed

Marinus

Vercauteren

Vandenberghe

et al. 2020

IREME

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Infrared thermography, force measurements, and oil flow visualizations are used to investigate the flow patterns around a cambered NACA16-409 airfoil at low Mach number. This cambered profile is widely used for propellers despite the lack of knowledge concerning its flow characteristics. The post-processing of thermograms relies on the analysis of the surface temperature gradient and identification of inflexion points in the temperature distribution. The observations made on the thermograms, based on the distribution of the temperature and Stanton number, are substantiated by the oil flow visualizations. RANS simulations with a transitional SST k-ω & γ turbulence model corroborate the analysis and deliver detailed insight in the flow around the airfoil. Depending on the angle of attack, three distinct flow patterns have been identified: laminar flow with early separation, laminar separation bubble with trailing edge separation, and turbulent flow with trailing edge separation. The shift between the last two regimes occurs sharply. The prediction capability of the transitional RANS simulations and XFOIL in terms of separation as well as reattachment location are compared with the experimental results. The force-coefficients dependency on the angle-of-attack, obtained by experiments, XFOIL, and RANS simulations, bear the traces from these flow patterns.

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Section: Introductionmentioning

confidence: 99%