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Article

Predicting Rotor Heat Transfer Using the Viscous Blade Element Momentum Theory and Unsteady Vortex Lattice Method

1
Thermo-Fluids for Transport Laboratory (TFT), Department of Mechanical Engineering, École de Technologie Supérieure, 1100 Notre-Dame St W, Montréal, QC H3C1K3, Canada
2
Anti-icing Materials International Laboratory (AMIL), Department of Applied Sciences, Univeristé du Québec à Chicoutimi (UQAC), 555 Boulevard de l’Université, Chicoutimi, QC G7H2B1, Canada
*
Author to whom correspondence should be addressed.
Aerospace 2020, 7(7), 90; https://doi.org/10.3390/aerospace7070090
Received: 20 March 2020 / Revised: 8 June 2020 / Accepted: 30 June 2020 / Published: 3 July 2020
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft)
Calculating the unsteady convective heat transfer on helicopter blades is the first step in the prediction of ice accretion and the design of ice-protection systems. Simulations using Computational Fluid Dynamics (CFD) successfully model the complex aerodynamics of rotors as well as the heat transfer on blade surfaces, but for a conceptual design, faster calculation methods may be favorable. In the recent literature, classical methods such as the blade element momentum theory (BEMT) and the unsteady vortex lattice method (UVLM) were used to produce higher fidelity aerodynamic results by coupling them to viscous CFD databases. The novelty of this research originates from the introduction of an added layer of the coupling technique to predict rotor blade heat transfer using the BEMT and UVLM. The new approach implements the viscous coupling of the two methods from one hand and introduces a link to a new airfoil CFD-determined heat transfer correlation. This way, the convective heat transfer on ice-clean rotor blades is estimated while benefiting from the viscous extension of the BEMT and UVLM. The CFD heat transfer prediction is verified using existing correlations for a flat plate test case. Thrust predictions by the implemented UVLM and BEMT agree within 2% and 80% compared to experimental data. Tip vortex locations by the UVLM are predicted within 90% but fail in extreme ground effect. The end results present as an estimate of the heat transfer for a typical lightweight helicopter tail rotor for four test cases in hover, ground effect, axial, and forward flight. View Full-Text
Keywords: unsteady vortex lattice method; blade element momentum theory; convective heat transfer; icing/de-icing; rotorcraft unsteady vortex lattice method; blade element momentum theory; convective heat transfer; icing/de-icing; rotorcraft
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MDPI and ACS Style

Samad, A.; Tagawa, G.B.S.; Morency, F.; Volat, C. Predicting Rotor Heat Transfer Using the Viscous Blade Element Momentum Theory and Unsteady Vortex Lattice Method. Aerospace 2020, 7, 90. https://doi.org/10.3390/aerospace7070090

AMA Style

Samad A, Tagawa GBS, Morency F, Volat C. Predicting Rotor Heat Transfer Using the Viscous Blade Element Momentum Theory and Unsteady Vortex Lattice Method. Aerospace. 2020; 7(7):90. https://doi.org/10.3390/aerospace7070090

Chicago/Turabian Style

Samad, Abdallah, Gitsuzo B.S. Tagawa, François Morency, and Christophe Volat. 2020. "Predicting Rotor Heat Transfer Using the Viscous Blade Element Momentum Theory and Unsteady Vortex Lattice Method" Aerospace 7, no. 7: 90. https://doi.org/10.3390/aerospace7070090

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