Experimental Investigations of Simulated Ice Accretions at High Reynolds Numbers in the Onera F1 Wind Tunnel.

Gilliot, Anne; Geiler, Claude; Monnier, Jean-Claude; Broeren, Andy P.; Addy, Harold E.; Wind, Fauga-Mauzac

doi:10.2514/6.2009-4265

Cited by 3 publications

(2 citation statements)

References 2 publications

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“…This research effort is modeled after a previous successful international collaboration that investigated aerodynamic effects and ice accretion simulation for airfoils and straight wings. [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18] The overall goal of the previous collaboration was to provide high-fidelity, full-scale, iced-airfoil aerodynamic data and validated subscalemodel simulation methods that produce the essential full-scale aerodynamic characteristics. The research was organized into six phases involving icing wind tunnel and aerodynamic wind tunnel experiments with both subscale and full-scale models using the NACA 23012 airfoil.…”

Section: Introductionmentioning

confidence: 99%

Swept-Wing Ice Accretion Characterization and Aerodynamics

Broeren

Potapczuk

Riley

et al. 2013

5th AIAA Atmospheric and Space Environments Conference

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and Boeing have embarked on a significant, collaborative research effort to address the technical challenges associated with icing on large-scale, three-dimensional swept wings. The overall goal is to improve the fidelity of experimental and computational simulation methods for swept-wing ice accretion formation and resulting aerodynamic effect. A seven-phase research effort has been designed that incorporates ice-accretion and aerodynamic experiments and computational simulations. As the baseline, full-scale, swept-wing-reference geometry, this research will utilize the 65% scale Common Research Model configuration. Ice-accretion testing will be conducted in the NASA Icing Research Tunnel for three hybrid swept-wing models representing the 20%, 64% and 83% semispan stations of the baseline-reference wing. Three-dimensional measurement techniques are being developed and validated to document the experimental ice-accretion geometries. Artificial ice shapes of varying geometric fidelity will be developed for aerodynamic testing over a large Reynolds number range in the ONERA F1 pressurized wind tunnel and in a smaller-scale atmospheric wind tunnel. Concurrent research will be conducted to explore and further develop the use of computational simulation tools for ice accretion and aerodynamics on swept wings. The combined results of this research effort will result in an improved understanding of the ice formation and aerodynamic effects on swept wings. The purpose of this paper is to describe this research effort in more detail and report on the current results and status to date.

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Section: Introductionmentioning

confidence: 99%

Swept-Wing Ice Accretion Characterization and Aerodynamics

Broeren

Potapczuk

Riley

et al. 2013

5th AIAA Atmospheric and Space Environments Conference

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“…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. 11,12 This dissertation is part of the larger NASA/ONERA/Illinois project to better understand iced-airfoil aerodynamics and to use this understanding to develop and validate sub-scale simulation methods.…”

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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Physical Analysis of the Separated Flow Around an Iced Airfoil Based on ZDES Simulations

Duclercq¹,

Brunet²,

Moëns³

2012

4th AIAA Atmospheric and Space Environments Conference

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This paper presents the results of a numerical study of the unsteady flow around a leading-edge iced airfoil. At first, we demonstrate the efficiency of the numerical model used for the unsteady computations, a Zonal Detached Eddy Simulation (ZDES), validated by experimental data. Then, the degradation of the aerodynamic performance due to the ice accretion is better predicted by the ZDES than by steady RANS-SA method. Besides the paper aims at improving the understanding of the unsteady phenomena related to the turbulent separated flows. Nomenclature ZDES : Zonal Detached Eddy Simulation RANS-SA : Reynolds-Averaged Navier-Stokes equations with Spalart-Allmaras turbulent model PIV : Particle Image Velocimetry c = airfoil chord length L y = airfoil span length h = height of the upper ice ridge x = chordwise position along the airfoil from the leading edge y = spanwise position (between -L y and 0) z = normal position from the airfoil chord line α = airfoil angle of attack P i = stagnation pressure in the wind tunnel U 0 = free stream velocity M = Mach number Re = Reynolds number based on chord length dt = time step df = frequency resolution for spectral analyses v x , v y , v z = x-, y-and z-components of the flow velocity C D= drag coefficient C y = force coefficient in the spanwise direction C L = lift coefficient C P = pressure coefficient Q = Q-criterion measuring vorticity in the flow C corrY = coefficient measuring the averaged correlation degree in the spanwise direction

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Experimental Investigations of Simulated Ice Accretions at High Reynolds Numbers in the Onera F1 Wind Tunnel.

Cited by 3 publications

References 2 publications

Swept-Wing Ice Accretion Characterization and Aerodynamics

Swept-Wing Ice Accretion Characterization and Aerodynamics

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

Physical Analysis of the Separated Flow Around an Iced Airfoil Based on ZDES Simulations

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