@inproceedings{b6b147cb98ca449aab4508b6195c95bc,
title = "Summary of ice shape geometric fidelity studies on an iced swept wing",
abstract = "Understanding the aerodynamic impact of swept-wing ice accretions is a crucial component of the design of modern aircraft. Computer-simulation tools are commonly used to approximate ice shapes, so the necessary level of detail or fidelity of those simulated ice shapes must be understood relative to high-fidelity representations of the ice. Previous tests were performed in the NASA Icing Research Tunnel to acquire high-fidelity ice shapes. Some of those ice shapes are based on aircraft certification requirements. From this database, full-span artificial ice shapes were designed and manufactured for both an 8.9%-scale and 13.3%-scale semispan wing model of the CRM65 which has been established as the full-scale baseline for this sweptwing project. These models were tested in the Walter H. Beech wind tunnel at Wichita State University and at the ONERA F1 facility, respectively. The data collected in the Wichita St. University wind tunnel provided a low-Reynolds number baseline study while the pressurized F1 facility produced data over a wide range of Reynolds and Mach numbers with the highest Reynolds number studied being approximately Re = 11.9×106. Three different fidelity representations were created based on three different icing conditions. Lower-fidelity ice shapes were created by lofting a smooth ice shape between cross-section cuts of the high-fidelity ice shape. Grit roughness was attached to this smooth ice shape as another fidelity variant. The data indicate that the geometric fidelity of the ice shapes resulted in significant differences in lift and drag. These results were similar at both facilities over the wide range of test conditions utilized.",
author = "Woodard, {Brian S.} and Broeren, {Andy P.} and Sam Lee and Lum, {Christopher W.} and Bragg, {Michael B.}",
note = "Funding Information: The authors gratefully acknowledge the assistance of many other individuals and organizations that made this work possible. Specific contributors to conducting these wind tunnel test �ampaigns and understanding the acquired data were Mark Potapczuk at NASA Glenn Research �enter, Kevin Ho, Stephanie Camello, and Navdeep Sandhu at the University of Washington, and Timothy Smith at the FAA. William Yoshida, an undergraduate student at the University of Illinois, wrote the computer code that generated the data for the surface-pressure contour plots. He also then created many of the figures necessary for this work. The engineers and technicians at both the ONERA F1 wind tunnel and the WSU Beech wind tunnel were extraordinarily helpful in keeping the tests running smoothly and efficiently. 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 are funded for this program by FAA grant 15-G-009 with support from Dr. James T. Riley. Funding Information: The authors gratefully acknowledge the assistance of many other individuals and organizations that made this work possible. Specific contributors to conducting these wind tunnel test campaigns and understanding the acquired data were Mark Potapczuk at NASA Glenn Research Center, Kevin Ho, Stephanie Camello, and Navdeep Sandhu at the University of Washington, and Timothy Smith at the FAA. William Yoshida, an undergraduate student at the University of Illinois, wrote the computer code that generated the data for the surface-pressure contour plots. He also then created many of the figures necessary for this work. The engineers and technicians at both the ONERA F1 wind tunnel and the WSU Beech wind tunnel were extraordinarily helpful in keeping the tests running smoothly and efficiently. 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 are funded for this program by FAA grant 15-G-009 with support from Dr. James T. Riley. Publisher Copyright: {\textcopyright} 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.; 10th AIAA Atmospheric and Space Environments Conference, 2018 ; Conference date: 25-06-2018 Through 29-06-2018",
year = "2018",
doi = "10.2514/6.2018-3494",
language = "English (US)",
isbn = "9781624105586",
series = "2018 Atmospheric and Space Environments Conference",
publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",
booktitle = "2018 Atmospheric and Space Environments Conference",
}