Ice Accretions on a Swept GLC-305 Airfoil

Vargas, Mario; Papadakis, Michael; Potapczuk, Mark G.; Addy, Harold E.; Sheldon, David W.; Giriunas, Julius A.

doi:10.4271/2002-01-1519

Cited by 19 publications

(12 citation statements)

References 4 publications

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“…Then we present rime-and glaze-ice results for a three-dimensional accretion on a swept and tapered wing with GLC-305 section. 9 The comparison between the simulation results and experimental ice shapes are included. However, the purpose of these comparisons is to demonstrate that our mesh evolution and deformation strategies are robust, even for complex ice shapes.…”

Section: Resultsmentioning

confidence: 99%

“…The flight and icing conditions for this case corresponded to Condition 5 in the report by Vargas et al 9 The freestream velocity and pressure were 111 m/s and 93382 Pa, respectively. The angle of attack was 4.5 • at the root of wing.…”

Section: Case 07200103: 2-min Glaze Ice Accretionmentioning

confidence: 90%

“…9 The wing has a constant GLC-305 section from root to tip, and a 28 • leading edge sweep. The halfspan of the wing is 1.52 m and chord length is 0.64 m and 0.256 m at the root and tip respectively.…”

Section: B Swept Tapered Wing With Glc-305 Cross Sectionmentioning

confidence: 99%

See 2 more Smart Citations

Robust Surface Evolution and Mesh Deformation for Three Dimensional Aircraft Icing Applications on a Swept GLC-305 Airfoil

Tong

Thompson

Arnoldus

et al. 2014

6th AIAA Atmospheric and Space Environments Conference

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This paper presents the application of a mesh generation strategy for problems involving deforming geometries produced by three-dimensional ice accretion simulations, which are more challenging than corresponding two-dimensional problems. A technique to deform a discrete surface as it evolves due to the accretion of ice is described. The surface evolution algorithm is based on a face-offseting approach. A fast algebraic technique to propagate the computed surface deformations into the surrounding volume mesh while maintaining geometric mesh quality is also presented. Results are presented for a complex glaze ice on a rectangular planform wing with a constant GLC-305 airfoil section and rime ice and glaze shapes on a swept, tapered GLC-305 wing also with a GLC-305 cross section.

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Section: Resultsmentioning

confidence: 99%

Section: Case 07200103: 2-min Glaze Ice Accretionmentioning

confidence: 90%

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Robust Surface Evolution and Mesh Deformation for Three Dimensional Aircraft Icing Applications on a Swept GLC-305 Airfoil

Tong

Thompson

Arnoldus

et al. 2014

6th AIAA Atmospheric and Space Environments Conference

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“…The total time exposed in icing condition is 7 minutes, thus total 42 iterations using CFD, droplet impingement and ice accretion solvers. Experimental tests [15] were also conducted in the NASA IRT. The ice shapes were observed to be in good agreement with each other.…”

Section: Validationmentioning

confidence: 99%

An efficient CFD-based method for aircraft icing simulation using a reduced order model

et al. 2011

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In-flight icing is a critical technical issue for aircraft safety and, in particular, the droplet impingement areas on aircraft surfaces must be investigated for anti-/de-icing devices. As a step toward the prediction of droplet impingement on aircraft, an Eulerian-based droplet impingement code that provides collection efficiency for air flows around an airfoil containing water droplets is developed. A computational fluid dynamics (CFD) solver was also developed to solve the clean airflow. Then, a proper orthogonal decomposition (POD) method, a reduced order model (ROM), that optimally captures the energy content from a large multi-dimensional data set is utilized to efficiently predict the collection efficiency and ice accretion shapes on an airfoil following the mean volume diameter, liquid water contents and angle of attacks. As a result it is shown that the collection efficiency and ice shapes were in good agreement with the simulated and predicted results.

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“…An icing test 21 was conducted at the NASA Glenn Icing Research Tunnel facility to generate five glaze ice shapes with complete and incomplete scallop features, and one rime ice shape. The ice accretions times ranged from NASA/TM-2005-2138362 to 22.5 minutes.…”

Section: A 28mentioning

confidence: 99%

Current Experimental Basis for Modeling Ice Accretions on Swept Wings

Vargas

2005

4th AIAA Theoretical Fluid Mechanics Meeting

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Ice Accretions on a Swept GLC-305 Airfoil

Cited by 19 publications

References 4 publications

Robust Surface Evolution and Mesh Deformation for Three Dimensional Aircraft Icing Applications on a Swept GLC-305 Airfoil

Robust Surface Evolution and Mesh Deformation for Three Dimensional Aircraft Icing Applications on a Swept GLC-305 Airfoil

An efficient CFD-based method for aircraft icing simulation using a reduced order model

Current Experimental Basis for Modeling Ice Accretions on Swept Wings

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