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oai:www.ideals.illinois.edu:2142/14714 2023-07-10 col_2142_5131 col_2142_14800 com_2142_5130 com_2142_14799 com_2142_234

Bragg, Michael B. Bragg, Michael B. Loth, Eric Selig, Michael S. Christensen, Kenneth T. Busch, Greg T. 2010-01-06T16:40:17Z 2010-01-06T16:40:17Z 2012-01-07T11:00:14Z 2010-01-06T16:40:17Z 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 aero- dynamic 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 Cl,max to within 2% and Cd,min to within 15%. Good qualitative agreement in the Cp 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 Cl,max and Cd. 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 found on the casting were necessary to improve simulation accuracy, resulting in Cl,max and Cd,min within 3% and 5% of the casting, respectively. Item withdrawn by Mark Zulauf (zulauf@illinois.edu) on 2009-12-01T14:18:42Z Item was in collections: University of Illinois Theses & Dissertations (ID: 1) No. of bitstreams: 1 Busch_Greg.pdf: 62824319 bytes, checksum: 1134f3bcb143cd21481a3a9e74595d2f (MD5) Made available in DSpace on 2010-01-06T16:40:17Z (GMT). No. of bitstreams: 3 Busch_Greg.pdf: 62824319 bytes, checksum: 1134f3bcb143cd21481a3a9e74595d2f (MD5) 1_Busch_Greg.pdf: 62824435 bytes, checksum: 4bd370d7a6224ff80efdd96f673ae6e0 (MD5) license.txt: 4059 bytes, checksum: 3ad41df29fdcdafc673f60353e2bbfce (MD5) Item marked as restricted to the 'UIUC Users [automated]' Group (id=2) by William Ingram (wingram2@illinois.edu) on 2010-01-06T16:40:29Z Item is restricted until 2012-01-06T16:40:25Z Item reinstated by Sarah Shreeves (sshreeve@illinois.edu) on 2012-01-07T11:00:14Z Item was in collections: University of Illinois Dissertations and Theses (ID: 204) Dissertations and Theses - Aerospace Engineering (ID: 682) No. of bitstreams: 4 1_Busch_Greg.pdf.txt: 386116 bytes, checksum: 27ca8799e4d05452bca60da1d662d853 (MD5) Busch_Greg.pdf: 62824319 bytes, checksum: 1134f3bcb143cd21481a3a9e74595d2f (MD5) 1_Busch_Greg.pdf: 62824435 bytes, checksum: 4bd370d7a6224ff80efdd96f673ae6e0 (MD5) license.txt: 4059 bytes, checksum: 3ad41df29fdcdafc673f60353e2bbfce (MD5) Item released from any restrictions by Sarah Shreeves (sshreeve@illinois.edu) on 2012-01-07T11:00:14Z http://hdl.handle.net/2142/14714 en Copyright 2009 Greg T. Busch ice accretion iced airfoil sub-scale simulation Experimental study of full-scale iced-airfoil aerodynamic performance using sub-scale simulations 2009-12 Aerospace Engineering 1615 Aerospace Engineering 4048 University of Illinois at Urbana-Champaign Dissertation Ph.D. PHD: Aerospace Engr -UIUC 10KS4048PHD