An algorithm for the aerodynamic analysis of rotating blades using a weak viscous-inviscid interaction method

Tinis, Mengu Umut

doi:10.22215/etd/2013-06247

Cited by 3 publications

(7 citation statements)

References 110 publications

(115 reference statements)

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“…The BET is very useful in reducing the problem of complexity, and the cost of accurately analyzing 3D flow effects such as spanwise flow. These methods can be augmented using empirical corrections to account for features such as spanwise flow and tip losses [15]. Combined with 2D panel methods, the blade loading can be determined very rapidly.…”

Section: Blade Element Momentum Theorymentioning

confidence: 99%

An Algorithm for Preliminary Aeroelastic Analysis of Composite Wind Turbine Blades

McFarlane¹

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Determining the structural response of composite horizontal axis wind turbine blades to wind loading is a challenging aeroelastic problem due to the coupling of unsteady aerodynamics and anisotropic structural dynamics. Methods such as Computational Fluid Dynamics (CFD) and Finite Element Analysis (FEA) are readily available through respected commercial software such as ANSYS, but are found to be unsuitable for the preliminary design phase in which many simulations are to be run, due to high computational time. A more efficient algorithm has been developed using a panel method for determining the unsteady aerodynamic blade loading, an anisotropic beam dynamics solver based on the Variational Asymptotic Beam Section (VABS) analysis tool developed by Khouli (2009) and the Ritz method, and the Blade Element Momentum Theory (BEMT).The algorithm was implemented in MATLAB and validated by comparing the results with coupled two-way Fluid-Structure Interaction (FSI) simulations performed using ANSYS Workbench 14. Strong agreement was found between the algorithm results and the corresponding ANSYS simulations. Impressively, the algorithm achieved computational times of less than 2% of the ANSYS simulations. The algorithm is considered a success and has been found to be suitable for use in the preliminary design phase of horizontal axis wind turbines and other flexible, lightweight structures.ii Acknowledgments I would like to thank my thesis co-supervisors: Professors Robert (The Eagle) G.Langlois, master of peer-reviewing, and Fred. F. Afagh, the king of troubleshooting, for their excellent support during this project. I would also like to thank my colleague, Mohamed El Sherif, who always supplied motivating tunes and helped us retain our sanity during the CFD simulations.iii

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Section: Blade Element Momentum Theorymentioning

confidence: 99%

An Algorithm for Preliminary Aeroelastic Analysis of Composite Wind Turbine Blades

McFarlane¹

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“…These references include experimental results over a large variety of airfoils, usually organized by application. Tinis [46] recently developed a viscous-inviscid interaction airfoil analysis tool at…”

Section: Airfoil Data Sourcesmentioning

confidence: 99%

“…This section details the main problem encountered with airfoil coefficient estimations provided by the VII algorithm [46], the subsequent efforts made to develop an empirical airfoil lift stall correction model and the final decision made to use XFOIL as the tool to generate two-dimensional airfoil data. Implemented airfoil data corrections for compressibility effects and limitations of the current implementation are also summarized.…”

Section: Generating Two-dimensional Airfoil Propertiesmentioning

confidence: 99%

“…As this tool was only recently developed, its results for a number of airfoils were compared to published experimental data in the Reynolds number range of interest. It was identified that the treatment of flow separation was not able to predict airfoil characteristics properly once the flow separated from the upper surface without reattachment, unless an empirical free-shear layer angle coefficient m was provided to define the angle at which the viscous shear layer separates from the airfoil surface[46]. The only solution provided to define this factor m, which would vary from one airfoil to the next and also change with angle of attack and flow condition, was reverse derivation from experimental data.…”

mentioning

confidence: 99%

“…Appendix A contains a number of figures showing the application of the VII algorithmcorrected with the lift stall estimation model presented in Section 3.1.1. Experimental data from References[17],[18] and[19] is included to allow an assessment of the overall performance of the tool in generating airfoil lift, drag and moment coefficients.In Reference[46] Tinis states that airfoil lift coefficients can be predicted well into the stalled region specifying 20°angle of attack as a limit for the S809 airfoil at Reynolds numbers 1 × 10 6 and 2 × 10 6 . The airfoil showed significant stall effects on the lift coefficients initiating at about 7°angle of attack.…”

mentioning

confidence: 99%

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Development of a Simulation and Optimization Framework for Improved Aerodynamic Performance of R/C Helicopter Rotor Blades

Wiebe¹

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To improve the performance characteristics of small unmanned rotorcraft systems based on commercially available radio controlled helicopter components the simulation and optimization framework Qoptr was developed. The framework's simulation modules model main rotor performance in hover using blade element momentum theory (BEMT) and in forward flight conditions employing a blade element theory (BET) approach. The forward flight module incorporates empirical induced inflow models and rigid blade motion. Two software packages based on viscous-inviscid interaction methods were evaluated on their ability to generate the low Reynolds number 2D aerodynamic airfoil performance coefficients required by the simulation modules at conditions applicable to large radio controlled helicopters. The Qoptr hover module was integrated into an optimization scheme using an algorithm from the MATLAB Optimization Toolbox. Starting from a rotor using typical commercial r/c rotor blades the optimization raised the rotor figure of merit from 0.56 to 0.70 by adjusting rotor speed, solidity and the spanwise distributions of blade pitch and chord length.

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A Novel 3D Viscous - Inviscid Interactive Method for Arbitrary Wings

Zhao

2018

2018 AIAA Aerospace Sciences Meeting

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An algorithm for the aerodynamic analysis of rotating blades using a weak viscous-inviscid interaction method

Cited by 3 publications

References 110 publications

An Algorithm for Preliminary Aeroelastic Analysis of Composite Wind Turbine Blades

An Algorithm for Preliminary Aeroelastic Analysis of Composite Wind Turbine Blades

Development of a Simulation and Optimization Framework for Improved Aerodynamic Performance of R/C Helicopter Rotor Blades

A Novel 3D Viscous - Inviscid Interactive Method for Arbitrary Wings

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