@inproceedings{edc09ef507b040cda44eff3a2e277711,
title = "Effect of geometric fidelity on the aerodynamics of a swept wing with scalloped ice accretion",
abstract = "The effect of geometric fidelity on the aerodynamics of a swept wing with a “scallop” ice shape was studied. Three geometric fidelity versions of the ice shape were studied. The High Fidelity ice shape maintained all of the highly 3D features of the scallop shape. The 3D Smooth ice shape was smoothly lofted over the High Fidelity shape in order to eliminate all of the local 3D feature. The third ice shape was the 3D Smooth ice shape with roughness grit attached to the surface. The two 3D Smooth versions of the ice shape exhibited a flowfield characterized by a leading edge separation bubble that rolled into a spanwise running vortex. The surface pressure data showed classic leading edge separation bubbles that are observed on 2D airfoils with leading edge horn ice shapes. The High Fidelity ice shape exhibited a flowfield characterized by streamwise vortices that formed downstream of the ice shape. The streamwise vortices observed downstream of the High Fidelity ice shape appeared to reduce the size of the separation suction peak observed downstream of the 3D Smooth ice shapes. This reduced the lift for the High Fidelity ice shape, when compared to the 3D Smooth ice shapes. However, these streamwise vortices may have allowed the flow to remain attached longer and slightly increased the stall angle of attack, even though the maximum lift was lower.",
author = "Sam Lee and Andy Broeren and Woodard, {Brian S.} and Bragg, {Michael B.}",
note = "Funding Information: The authors would like to thank the many key collaborators without whom this work would not have been possible. Mark Potapczuk at NASA, Chris Lum, Kevin Ho, and Reza Soltani at the University of Washington, and Tim Smith at FAA provided key support during the test. The authors would also like to acknowledge the staff at the Walter H. Beech Memorial Wind Tunnel at Wichita State University for their outstanding support. This work was supported through international and interagency agreements between NASA, the FAA, and ONERA. The NASA-supported portion of this research was originally funded under the Atmospheric Environment Safety Technologies Project of the Aviation Safety Program with continued support under the Advanced Air Transport Technology and Aeronautics Evaluation and Test Capabilities Projects of the Advanced Air Vehicles Program. The Universities of Washington and Illinois were funded for this program by FAA grant 15-G-009 with support from Dr. James T. Riley. Publisher Copyright: {\textcopyright} 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.; AIAA AVIATION 2020 FORUM ; Conference date: 15-06-2020 Through 19-06-2020",
year = "2020",
doi = "10.2514/6.2020-2847",
language = "English (US)",
isbn = "9781624105982",
series = "AIAA AVIATION 2020 FORUM",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
booktitle = "AIAA AVIATION 2020 FORUM",
}