Effect of High-Fidelity Ice Accretion Simulations on the Performance of a Full-Scale Airfoil Model

Broeren, Andy P.; Bragg, Michael B.; Addy, Harold E.; Lee, Sam; Moëns, Frédéric; Guffond, Didier

doi:10.2514/6.2008-434

Cited by 20 publications

(43 citation statements)

References 9 publications

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“…Note that M was not assumed equal to zero during the testing of Broeren et al 9 on the full-scale ice castings at high Re, so the wind-tunnel corrections used for those tests were slightly different than those discussed here which were used during the sub-scale simulation tests.…”

Section: Wind Tunnel Correctionsmentioning

confidence: 99%

“…4 The dominant feature is a long separation bubble 13 generated near the tip of the horn ( Fig. 2.10 The time-averaged C p distribution measured by Broeren et al 9 for a NACA 23012 airfoil with a horn-ice casting is shown in Fig. 2.11 for angles of attack prior to and after stall.…”

Section: Horn-ice Flowfieldmentioning

confidence: 99%

“…Broeren et al 9,15 measured the aerodynamic performance degradation of a 72-inch chord NACA 23012 airfoil using high-fidelity, full-scale ice castings representative of each type of iced-airfoil flowfield at near-flight Reynolds numbers. Representative data from this testing are shown in Fig.…”

Section: Classification Of Iced-airfoil Flowfieldsmentioning

confidence: 99%

“…Full-scale aerodynamic testing was conducted by Broeren et al 9 in the ONERA F1 wind tunnel ( Fig. 3.1 All sub-scale aerodynamic testing was conducted in a subsonic, low-turbulence, openreturn wind tunnel at the University of Illinois at Urbana-Champaign ( Fig.…”

Section: Wind Tunnelmentioning

confidence: 99%

“…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%

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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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Section: Wind Tunnel Correctionsmentioning

confidence: 99%

Section: Horn-ice Flowfieldmentioning

confidence: 99%

Section: Classification Of Iced-airfoil Flowfieldsmentioning

confidence: 99%

Section: Wind Tunnelmentioning

confidence: 99%