Results From a Full-Scale Propeller Icing Test

Dumont, Christopher; Hughes, W. J.; Pellicano, Paul; Atlanta, Faa; Smith, Timothy G.; Riley, James T.

doi:10.2514/6.2008-432

Cited by 3 publications

(3 citation statements)

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“…The first part briefly describes the run conditions of the icing test by Dumont et al 2 which were investigated in the current study. The next part discusses LEWICEpredicted ice geometries at the mid-boot, 50%, and 75% propeller blade sections for each of the three runs shown in Table 1.…”

Section: Resultsmentioning

confidence: 99%

“…1 for three different sets of icing conditions, designated Run 3B (R3B), Run 19A (R19A) and Run 21 (R21, an SLD condition). In that test, after each icing run, an ice knife was used to slice the ice so that a template could be used to trace the ice accretion; more details on the procedure used is provided by Dumont et al 2 Initial investigations using LEWICE during the current study showed considerable discrepancies between the tracings and the LEWICE results. It was found that these discrepancies likely resulted from ice shedding from the propeller blade and that shedding was a significant factor in this study, so some basic procedures were developed to attempt to model this phenomenon in LEWICE.…”

Section: Prediction Of Blade-section Ice Geometrymentioning

confidence: 96%

“…The current study was the third phase of an FAA investigation to better understand the effects of ice accretion on propeller performance. The first phase was an experimental icing test conducted at McKinley Climatic Laboratory at Eglin Air Force Base on a full-scale propeller; this phase is discussed in detail by Dumont et al 2 The second phase used ice accretion documentation obtained during the icing test (e.g., ice tracings, photographs, and video) to determine propeller blade-section aerodynamic performance degradation in icing conditions using artificial ice shapes. The iced blade-section performance was then related to the iced-propeller performance using a bladeelement code; this work is discussed by Busch,Bragg,and Broeren.…”

Section: Introductionmentioning

confidence: 99%

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Computational Prediction of Propeller Performance in Icing Conditions

Busch

Bragg

2010

AIAA Atmospheric and Space Environments Conference

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The objective of this investigation was to develop a computational methodology to quantify propeller performance in icing conditions and to identify areas where additional research is required. Propeller blade-section ice geometry was predicted using the ice accretion code LEWICE, the corresponding degradation in blade-section aerodynamic performance was predicted using the RANS code Fluent, and the blade-section performance was correlated to propeller performance with a blade-element code utilizing vortex theory. The results of this process were compared to experimental data obtained during a full-scale propeller icing test conducted at McKinley Climatic Laboratory at Eglin AFB. Ice shedding was found to be significant during these tests, and LEWICE was only able to accurately predict blade-section ice geometries by accounting for this shedding using experimental observations. Fluent predictions of blade-section aerodynamic performance were compared with experimental measurements obtained with artificial ice shapes in an earlier part of this investigation; agreement ranged from poor to good, depending on the blade section and ice geometry. The resulting predictions in clean and iced propeller performance were within 10% of the experimentally-measured values for two of the three icing conditions presented, and within 17% for the third set of conditions. This study has identified areas where research is needed to improve the accuracy of the predictions.

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Section: Resultsmentioning

confidence: 99%

Section: Prediction Of Blade-section Ice Geometrymentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

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Computational Prediction of Propeller Performance in Icing Conditions

Busch

Bragg

2010

AIAA Atmospheric and Space Environments Conference

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Aircraft design cues on ice protection and air data systems

Saglam

2011

2011 IEEE International Conference on Mechatronics

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Current aircraft designs include many different aspects from many different topics. In this paper, some brief and fun damental information on selection criteria of aircraft systems on specific aircraft is given, the system integration process and its needing on aircraft platforms are analyzed. It's clear that even a small aircraft includes very complex systems from different varieties. This paper makes an introduction to this process to show how a selection should be made in a safe and cost-effective way. Throughout the paper the densest data would be on trainer aircraft. As generically stated, aviation history dates back to early 20th century. Today, design criteria on each system have been evolved, and all designer companies need to find most efficient, most sustainable systems in aircraft design. This de pends on which kind of platform will employ this system on which purpose. The costs through development process are getting higher each day by day in aviation. In the mean time, the system integration is getting harder for aircraft developer com panies. Each complex system comes further on and integration of these systems is getting harder. Thus, the main function is to select most simple, functional system to easily integrate with other systems.

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