Abstract
Language | English |
---|---|
Pages | 1611 - 1624 |
Number of pages | 14 |
Journal | Journal of Aircraft |
Volume | 52 |
Issue number | 5 |
DOIs | |
Publication status | Published - 30 Sep 2015 |
Externally published | Yes |
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Keywords
- supercooled large droplets
- splashing
- bouncing
Cite this
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Eulerian modeling of supercooled large droplet splashing and bouncing. / Bilodeau, David ; Habashi, Wagdi; Baruzzi, Guido; Fossati, Marco.
In: Journal of Aircraft, Vol. 52, No. 5, 30.09.2015, p. 1611 - 1624.Research output: Contribution to journal › Article
TY - JOUR
T1 - Eulerian modeling of supercooled large droplet splashing and bouncing
AU - Bilodeau, David
AU - Habashi, Wagdi
AU - Baruzzi, Guido
AU - Fossati, Marco
PY - 2015/9/30
Y1 - 2015/9/30
N2 - A conservative Eulerian numerical approach for modeling postimpact Supercooled Large Droplets undergoing splashing and bouncing on aircraft surfaces is presented. The approach introduces the effect of the postimpact droplets by successive solutions of the conservation equations. Two models have been selected to identify the droplet splashing and bouncing conditions, and to provide initial conditions for the reinjected water. The method has been applied to droplet impingement in Supercooled Large Droplet conditions on clean and iced NACA 23012 geometries, as well as the MS(1)-0317 airfoil, and the results have been compared to experimental data. Good agreement is observed for both impingement limits and collection efficiency. Additionally, the method has been applied to a three-element high-lift configuration operating in one of the proposed Appendix O Supercooled Large Droplet environments to demonstrate the danger posed by the re-impingement of splashing and bouncing droplets on complex interacting aerodynamic components.
AB - A conservative Eulerian numerical approach for modeling postimpact Supercooled Large Droplets undergoing splashing and bouncing on aircraft surfaces is presented. The approach introduces the effect of the postimpact droplets by successive solutions of the conservation equations. Two models have been selected to identify the droplet splashing and bouncing conditions, and to provide initial conditions for the reinjected water. The method has been applied to droplet impingement in Supercooled Large Droplet conditions on clean and iced NACA 23012 geometries, as well as the MS(1)-0317 airfoil, and the results have been compared to experimental data. Good agreement is observed for both impingement limits and collection efficiency. Additionally, the method has been applied to a three-element high-lift configuration operating in one of the proposed Appendix O Supercooled Large Droplet environments to demonstrate the danger posed by the re-impingement of splashing and bouncing droplets on complex interacting aerodynamic components.
KW - supercooled large droplets
KW - splashing
KW - bouncing
UR - http://arc.aiaa.org/doi/10.2514/1.C033023#_i33
U2 - 10.2514/1.C033023
DO - 10.2514/1.C033023
M3 - Article
VL - 52
SP - 1611
EP - 1624
JO - Journal of Aircraft
T2 - Journal of Aircraft
JF - Journal of Aircraft
SN - 0021-8669
IS - 5
ER -