Results of an icing test on a NACA 0012 airfoil in the NASA Lewis Icing Research Tunnel

Shin, Jaiwon; Bond, Thomas H.

doi:10.2514/6.1992-647

Cited by 68 publications

(45 citation statements)

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“…Thus, there is some variation from run to run in ice accretion geometry under nominally identical icing conditions. This variation has been documented in several earlier studies, [81][82][83][84] In the current study, the non-repeatability of ice shapes was not examined in detail, as the goal was to develop a sub-scale simulation methodology for modeling the iced-airfoil performance of a given ice shape geometry rather than to determine the aerodynamic performance degradation associated with a given set of icing conditions. This second problem was investigated in an earlier study by Campbell et al, [85][86][87] who related not just iced-airfoil performance but also aircraft performance (i.e., stall speed) to icing cloud conditions.…”

Section: Ice Simulation Geometry Uncertaintymentioning

confidence: 83%

“…Uncertainties in ice geometry should also be considered when using sub-scale methods, as previous studies 24,30,81,87 discussed in Section 2.2.2 have shown that variations in C l,max as large as 13-18% and even larger variations in C d may result from using tracings taken at different spanwise stations, icing tunnel repeatability issues, or very small variations in icing cloud conditions. These latter two issues are associated with the ice accretion process rather than the aerodynamic simulation of a given ice shape, and the corresponding uncertainties are Table 5.1 Summary of aerodynamic fidelity of geometrically-scaled two-dimensional ice casting simulations.…”

Section: Discussionmentioning

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: Ice Simulation Geometry Uncertaintymentioning

confidence: 83%

Section: Discussionmentioning

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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“…The HPC model was applied to the complete 171 sets of data for model validation 3,5,6 . The comparison between the calculated value and the experimentally measured results is shown in Figure 1.…”

Section: A Drag Calculation and Correlation To Experimental Datamentioning

confidence: 99%

“…Flemming and Lednicer extensively investigated high-speed ice accretion on various rotorcraft airfoils 3 . Wind tunnel airfoil drag measurements with ice shapes obtained under comprehensive icing conditions have been carried out by Shaw et al 4 , Olsen et al 5 , and Shin & Bond 6 . Simulated ice shapes have also been used for dry air wind tunnel aerodynamics testing 7,8 .…”

Section: Introductionmentioning

confidence: 99%

Analytical and Experimental Determination of Airfoil Performance Degradation Due to Ice Accretion

Han

Palacios

2012

4th AIAA Atmospheric and Space Environments Conference

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A physics-based, empirical correlation between icing conditions and corresponding drag coefficient was developed for NACA 0012 airfoil and compared to other three existing prediction methods. The correlation was developed based on experimental aerodynamics database of iced airfoils and derived using statistical methods. The correlation model also provides drag coefficients for varying angles of attack under a given icing condition. The calculated drag coefficients matched (33.40% mean absolute deviation) with reference data from three different experimental databases. To validate the proposed degradation model and to further extend the database for helicopter rotor performance degradation, rotating ice accretion experiments were conducted. Four ice shapes obtained at the NASA Icing Research Center were reproduced on a 21-inch chord, 4.5-feet radius NACA 0012 rotor blade at the Adverse Environment Rotor Test Stand facility. Ice shape molding and casting techniques were introduced to capture delicate ice features such as ice feathers. The iced airfoil castings were tested in a dry-air wind tunnel. Performance degradation was compared between the four iced models and the clean airfoil. The effect of ice feathers on drag degradation was investigated. Ice feather formation can account for up to 25% of the drag introduced by ice accretion prior to stall. Comparison between the proposed analytical determination method and experimental results from both rotor ice testing and icing wind tunnel testing showed to be satisfactory, ranging from 25% to 6% depending on the icing condition. NomenclatureA c = Accumulation parameter, dimensionless AOA, α = Angle of attack, degree C = Airfoil chord, m Cd = Drag coefficient, dimensionless Cl = Lift coefficient, dimensionless Cm = Pitching moment coefficient, dimensionless d = Characteristic Length, twice the leading edge radius K 0 = Modified inertia parameter, dimensionless LWC = Cloud Liquid Water Content, g/m 3 Ma = Mach number, dimensionless MVD, δ = Water droplet Medium Volume Diameter, µm r = Airfoil leading edge radius, percentage of chord Re = Reynolds number, dimensionless RPM = Rotational speed, revolution per minute T = Static Temperature, K V = Free-stream velocity of air, m/s β 0 = Collection efficiency at stagnation line, dimensionless ΔCd = Drag coefficient increment, dimensionless ρ = Density, kg/m 3 τ = Icing time, minute

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“…Therefore, the application of (3.21) to the equations of motion and the state space models can be written simply as, 24) for the equations of motion and, 25) for the elements of the state space model's system matrix A ∈ R n×n and control matrix B ∈ R n×m .…”

Section: Modeling Ice Accretion Icing Effects Modelmentioning

confidence: 99%

Adaptive Control of Aircraft in Uncertain Icing Conditions

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Results of an icing test on a NACA 0012 airfoil in the NASA Lewis Icing Research Tunnel

Cited by 68 publications

References 0 publications

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

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

Analytical and Experimental Determination of Airfoil Performance Degradation Due to Ice Accretion

Adaptive Control of Aircraft in Uncertain Icing Conditions

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