Validation of New Formulations for Propeller Analysis

Morgado, J.; Silvestre, Miguel; Páscoa, José

doi:10.2514/1.b35240

Cited by 33 publications

(30 citation statements)

References 10 publications

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“…At low advance ratios in particular, large sections of each propeller blade may be stalled and face very low Reynolds numbers. Both conditions lead to difficulties in modelling propeller performance (7,8) . Blade element methods are widely used to model propeller aerodynamics due to their simplicity, efficiency and relatively good accuracy (7,8) .…”

Section: Introductionmentioning

confidence: 99%

“…Both conditions lead to difficulties in modelling propeller performance (7,8) . Blade element methods are widely used to model propeller aerodynamics due to their simplicity, efficiency and relatively good accuracy (7,8) . However, if propeller sections are stalled or face low Reynolds number airflow, this accuracy begins to degrade.…”

Section: Introductionmentioning

confidence: 99%

“…However, if propeller sections are stalled or face low Reynolds number airflow, this accuracy begins to degrade. This degradation occurs since the aerodynamic models coupled with blade element methods are usually simplistic (7,8) . Aerodynamic data is often only provided for an assumed aerofoil section between the stall angles and for a single (typically high) Reynolds number.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Blade element momentum theory extended to model low Reynolds number propeller performance

MacNeill

Verstraete

2017

Aeronaut. j.

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Propellers are the predominant propulsion source for small unmanned aerial vehicles. At low advance ratios, large sections of the propeller blade can be stalled, and the Reynolds number faced by each blade can be low. This leads to difficulties in modelling propeller performance, as the aerodynamic models coupled with blade element methods usually only provide aerodynamic data for an assumed aerofoil section, for a small angle-of-attack range and for a single Reynolds number, while rotational effects are often ignored. This is specifically important at low advance ratios, and a consistent evaluation of the applicability of various methods to improve aerodynamic modelling is not available. To provide a systematic appraisal, three-dimensional (3D) scanning is used to obtain the aerofoil sections that make up a propeller blade. An aerodynamic database is formed using each extracted aerofoil section, across a wide range of angles of attack and Reynolds numbers. These databases are then modified to include the effects of rotation. When compared with experimental results, significant improvement in modelling accuracy is shown at low advance ratios relative to a generic blade element-momentum model, particularly for smaller propellers. Notably, when considering small propeller performance, efficiency modelling is improved from within 30% relative to experimental data to within 5% with the use of the extended blade element momentum theory method. The results show that combining Viterna and Corrigan flat plate theory with the Corrigan and Schillings stall delay model consistently yields the closest match with experimental data.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Blade element momentum theory extended to model low Reynolds number propeller performance

MacNeill

Verstraete

2017

Aeronaut. j.

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“…JBLADE [28][29][30][31][32] is a numerical open-source propeller design and analysis software written in the C++/QML programming language [33]. The code is based on QBLADE [34,35] and XFLR5 [36] codes.…”

Section: Jblade Overviewmentioning

confidence: 99%

High altitude propeller design and analysis

Morgado

Abdollahzadeh

Silvestre

et al. 2015

Aerospace Science and Technology

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“…Morgado et al [11,12] developed a new propeller and analysis tool that can estimate the performance of a propeller. The software uses an improved blade element momentum for every blade section.…”

Section: Introductionmentioning

confidence: 99%

3D CFD Simulation and Experimental Validation of Small APC Slow Flyer Propeller Blade

Kutty

Rajendran

2017

Aerospace

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Abstract:The current work presents the numerical prediction method to determine small-scale propeller performance. The study is implemented using the commercially available computational fluid dynamics (CFD) solver, FLUENT. Numerical results are compared with the available experimental data for an advanced precision composites (APC) Slow Flyer propeller blade to determine the discrepancy of the thrust coefficient, power coefficient, and efficiencies. The study utilized unstructured tetrahedron meshing throughout the analysis, with a standard k-ω turbulence model. The Multiple Reference Frame model was also used to consider the rotation of the propeller toward its local reference frame at 3008 revolutions per minute (RPM). Results show reliable thrust coefficient, power coefficient, and efficiency data for the case of low advance ratio and an advance ratio less than the negative thrust conditions.

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Validation of New Formulations for Propeller Analysis

Cited by 33 publications

References 10 publications

Blade element momentum theory extended to model low Reynolds number propeller performance

Blade element momentum theory extended to model low Reynolds number propeller performance

High altitude propeller design and analysis

3D CFD Simulation and Experimental Validation of Small APC Slow Flyer Propeller Blade

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