Aerodynamic characteristics of a symmetric NACA section with simulated ice shapes

Papadakis, Michael; Alansatan, Sait; Wong, See-Cheuk

doi:10.2514/6.2000-98

Cited by 16 publications

(17 citation statements)

References 4 publications

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“…To this purpose, time-dependent simulations of the spoiler-ice test are performed at different angle of attack [9]. The results are validated with experimental data.…”

Section: Introductionmentioning

confidence: 95%

“…The second is called "glaze ice," which is generated in the temperature range −10 to 0 ∘ C. On glaze ice conditions, droplets gradually freeze while moving along the body, so-called runback [8]. Glaze ice accretion is often characterized by the presence of large protuberances, commonly known as glaze horns (Figure 1), which can cause flow separation downstream of the horns [9]. On iced airfoils, the boundary layer separates near the top of the horn, due to the pressure gradient produced by the large discontinuity in the surface geometry.…”

Section: Introductionmentioning

confidence: 99%

“…Leading edge glaze ice accretions characteristically may consist of an upper and lower surface horns, called double-horn ice. In 2000, experimental data were provided for the NACA 0011 airfoil with simulated glaze ice shapes on both upper and lower surfaces [9]. The ice accretions can also be simulated with wooden forward-facing quarter-round shapes.…”

Section: Introductionmentioning

confidence: 99%

“…In the previous study [20], steady state simulations were performed to investigate the mean flow characteristics. The aerodynamic performance coefficients and pressure profile were determined with CFD and compared with the available measurements in [9]. The steady state simulations were not found to be reliable to calculate the loads in the case of iced airfoil.…”

Section: Introductionmentioning

confidence: 99%

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Time-Dependent Effects of Glaze Ice on the Aerodynamic Characteristics of an Airfoil

Tabatabaei

Cervantes

Trivedi

2018

International Journal of Rotating Machinery

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The main objective of this study is to estimate the dynamic loads acting over a glaze-iced airfoil. This work studies the performance of unsteady Reynolds-averaged Navier-Stokes (URANS) simulations in predicting the oscillations over an iced airfoil. The structure and size of time-averaged vortices are compared to measurements. Furthermore, the accuracy of a two-equation eddy viscosity turbulence model, the shear stress transport (SST) model, is investigated in the case of the dynamic load analysis over a glaze-iced airfoil. The computational fluid dynamic analysis was conducted to investigate the effect of critical ice accretions on a 0.610 m chord NACA 0011 airfoil. Leading edge glaze ice accretion was simulated with flat plates (spoiler-ice) extending along the span of the blade. Aerodynamic performance coefficients and pressure profiles were calculated and validated for the Reynolds number of 1.83 × 106. Furthermore, turbulent separation bubbles were studied. The numerical results confirm both time-dependent phenomena observed in previous similar measurements: (1) low-frequency mode, with a Strouhal number Sth≈0,013–0.02, and (2) higher frequency mode with a Strouhal number StL≈0,059–0.69. The higher frequency motion has the same characteristics as the shedding mode and the lower frequency motion has the flapping mode characteristics.

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“…To this purpose, time-dependent simulations of the spoiler-ice test are performed at different angle of attack [9]. The results are validated with experimental data.…”

Section: Introductionmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Time-Dependent Effects of Glaze Ice on the Aerodynamic Characteristics of an Airfoil

Tabatabaei

Cervantes

Trivedi

2018

International Journal of Rotating Machinery

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“…Simple-geometry simulations tend to have lower cost than 2-D smooth simulations and are better-suited for for use in parametric studies. [16][17][18]47 Simple-geometry simulations are generally considered to be of a lower geometric fidelity than 2-D smooth simulations. Surface roughness is frequently added to both 2-D smooth and simple-geometry simulations to increase simulation fidelity.…”

Section: Ice Simulation Geometry Uncertaintymentioning

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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Iced-airfoil aerodynamics

Bragg¹,

Broeren²,

Blumenthal³

2005

Progress in Aerospace Sciences

327

190

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Aerodynamic characteristics of a symmetric NACA section with simulated ice shapes

Cited by 16 publications

References 4 publications

Time-Dependent Effects of Glaze Ice on the Aerodynamic Characteristics of an Airfoil

Time-Dependent Effects of Glaze Ice on the Aerodynamic Characteristics of an Airfoil

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

Iced-airfoil aerodynamics

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