Airfoil Ice-Accretion Aerodynamic Simulation

Bragg, Michael B.; Broeren, Andy P.; Addy, Harold E.; Potapczuk, Mark G.; Guffond, Didier; Montreuil, Emmanuel

doi:10.2514/6.2007-85

Cited by 52 publications

(45 citation statements)

References 18 publications

(29 reference statements)

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“…Recent iced aerodynamics simulation studies provide a significant body of knowledge examining the effects of ice accretion (size, shape, roughness, 3-Dity) on drag increase, lift loss, and stall characteristics of a NACA 23012 airfoil at full-scale and subscale geometry and Reynolds numbers [13]. Figure 2 illustrates the change in performance characteristics with different ice shapes at Re 1: 8 10 6 .…”

Section: Modeling Icing Effects: Wind-tunnel Resultsmentioning

confidence: 99%

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Current Methods Modeling and Simulating Icing Effects on Aircraft Performance, Stability, Control

Ratvasky

Barnhart

Lee³

2010

Journal of Aircraft

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Icing alters the shape and surface characteristics of aircraft components, which results in altered aerodynamic forces and moments caused by air flow over those iced components. The typical effects of icing are increased drag, reduced stall angle of attack, and reduced maximum lift. In addition to the performance changes, icing can also affect control surface effectiveness, hinge moments, and damping. These effects result in altered aircraft stability and control and flying qualities. Over the past 80 years, methods have been developed to understand how icing affects performance, stability, and control. Emphasis has been on wind-tunnel testing of two-dimensional subscale airfoils with various ice shapes to understand their effect on the flowfield and ultimately the aerodynamics. This research has led to wind-tunnel testing of subscale complete aircraft models to identify the integrated effects of icing on the aircraft system in terms of performance, stability, and control. Data sets of this nature enable pilot-in-the-loop simulations to be performed for pilot training or engineering evaluation of system failure impacts or control system design.

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Section: Modeling Icing Effects: Wind-tunnel Resultsmentioning

confidence: 99%

“…1. They were accreted on a NACA 23012 airfoil model in the NASA Icing Research Tunnel [13]. Figure 1a shows an example of a horn ice shape that forms at temperatures near freezing, where impinging water droplets can flow before freezing.…”

Section: Airframe Icing: How It Formsmentioning

confidence: 99%

Current Methods Modeling and Simulating Icing Effects on Aircraft Performance, Stability, Control

Ratvasky

Barnhart

Lee³

2010

Journal of Aircraft

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“…Recent iced aerodynamics simulation studies provide a significant body of knowledge examining the effects of ice accretion (size, shape, roughness, three-dimensionality) on drag increase, lift loss, and stall characteristics of a NACA 23012 airfoil at full-scale and sub-scale geometry and Reynolds numbers (ref. 13). Figure 2 illustrates the change in performance characteristics with different ice shapes.…”

Section: Modeling Icing Effects: Wind Tunnel Results From Two-dimentioning

confidence: 99%

“…They were accreted on a NACA 23012 airfoil model in the NASA Icing Research Tunnel (ref. 13). Figure 1(a) shows an example of a horn ice shape that forms at temperatures near freezing, where impinging water droplets can flow prior to freezing.…”

Section: Airframe Icing-how It Formsmentioning

confidence: 99%

Current Methods for Modeling and Simulating Icing Effects on Aircraft Performance, Stability and Control

Ratvasky

Barnhart

Lee³

2008

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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“…Recently, a major joint NASA/ONERA/Illinois research program developed and validated methods of categorizing and simulating ice accretion on wind tunnel airfoil models. 3 Different types of ice accretion were identified and classified based on key flowfield features, 4 and methods of constructing sub-scale simulations for each of these types of accretion were developed using sub-scale icing and aerodynamic airfoil models at low Reynolds number. 1, 5-8 These methods were then validated using iced-airfoil performance data obtained by Broeren et al 9 and CassouDeSalle et al 10 on a full-scale airfoil model at near-flight Reynolds numbers.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of Full-Scale Iced Airfoil Aerodynamic Performance Using Sub-Scale Simulations

Busch

Bragg

2009

1st AIAA Atmospheric and Space Environments Conference

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Determining the aerodynamic effects of ice accretion on aircraft surfaces is an important step in aircraft design and certification. The goal of this work was to develop a complete sub-scale wind tunnel simulation methodology based on knowledge of the detailed iced-airfoil flowfield that allows the accurate measurement of aerodynamic penalties associated with the accretion of ice on an airfoil and to validate this methodology using full-scale iced-airfoil performance data obtained at near-flight Reynolds numbers. In earlier work, several classifications of ice shape were developed based on key aerodynamic features in the iced-airfoil flowfield: ice roughness, streamwise ice, horn ice, and tall and short spanwise-ridge ice. Castings of each of these classifications were acquired on a full-scale NACA 23012 airfoil model and the aerodynamic performance of each was measured at a Reynolds number of 12.0 x 10 6 and a Mach number = 0.20. In the current study, sub-scale simple-geometry and 2-D smooth simulations of each of these castings were constructed based on knowledge of iced-airfoil flowfields. The effects of each simulation on the aerodynamic performance of an 18-inch chord NACA 23012 airfoil model was measured in the University of Illinois 3 x 4 ft. wind tunnel at a Reynolds number of 1.8 x 10 6 and a Mach number of 0.18 and compared with that measured for the corresponding full-scale casting at high Reynolds number. Geometrically-scaled simulations of the horn-ice and tall spanwise-ridge ice castings modeled C l,max to within 2% and C d,min to within 15%. Good qualitative agreement in the C p distributions suggests that important geometric features such as horn and ridge height, surface location, and angle with respect to the airfoil chordline were appropriately modeled. Geometrically-scaled simulations of the ice roughness, streamwise ice, and short-ridge ice tended to have conservative C l,max and C d . The aerodynamic performance of simulations of these types of accretion was found to be sensitive to roughness height and concentration. Scaled roughness heights smaller than those ii found on the casting were necessary to improve simulation accuracy, resulting in C l,max and C d,min within 3% and 5% of the casting, respectively.iii

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Airfoil Ice-Accretion Aerodynamic Simulation

Cited by 52 publications

References 18 publications

Current Methods Modeling and Simulating Icing Effects on Aircraft Performance, Stability, Control

Current Methods Modeling and Simulating Icing Effects on Aircraft Performance, Stability, Control

Current Methods for Modeling and Simulating Icing Effects on Aircraft Performance, Stability and Control

Experimental Study of Full-Scale Iced Airfoil Aerodynamic Performance Using Sub-Scale Simulations

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