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Low-Reynolds Number Aerodynamics of an 8.9 Percent Scale Semispan Swept Wing for Assessment of Icing Effects
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Author and Affiliation:
Broeren, Andy P.(NASA Glenn Research Center, Cleveland, OH United States)
Woodard, Brian S.(Illinois Univ., Urbana-Champaign, IL, United States)
Diebold, Jeffrey M.(Illinois Univ., Urbana-Champaign, IL, United States)
Moens, Frederic(Office National d'Etudes et de Recherches Aerospatiales, French Aerospace Lab., Meudon, France)
Abstract: Aerodynamic assessment of icing effects on swept wings is an important component of a larger effort to improve three-dimensional icing simulation capabilities. An understanding of ice-shape geometric fidelity and Reynolds and Mach number effects on the iced-wing aerodynamics is needed to guide the development and validation of ice-accretion simulation tools. To this end, wind-tunnel testing and computational flow simulations were carried out for an 8.9 percent-scale semispan wing based upon the Common Research Model airplane configuration. The wind-tunnel testing was conducted at the Wichita State University 7 by 10 ft Beech wind tunnel from Reynolds numbers of 0.8×10(exp 6) to 2.4×10(exp 6) and corresponding Mach numbers of 0.09 to 0.27. This paper presents the results of initial studies investigating the model mounting configuration, clean-wing aerodynamics and effects of artificial ice roughness. Four different model mounting configurations were considered and a circular splitter plate combined with a streamlined shroud was selected as the baseline geometry for the remainder of the experiments and computational simulations. A detailed study of the clean-wing aerodynamics and stall characteristics was made. In all cases, the flow over the outboard sections of the wing separated as the wing stalled with the inboard sections near the root maintaining attached flow. Computational flow simulations were carried out with the ONERA elsA software that solves the compressible, threedimensional RANS equations. The computations were carried out in either fully turbulent mode or with natural transition. Better agreement between the experimental and computational results was obtained when considering computations with free transition compared to turbulent solutions. These results indicate that experimental evolution of the clean wing performance coefficients were due to the effect of three-dimensional transition location and that this must be taken into account for future data analysis. This research also confirmed that artificial ice roughness created with rapid-prototype manufacturing methods can generate aerodynamic performance effects comparable to grit roughness of equivalent size when proper care is exercised in design and installation. The conclusions of this combined experimental and computational study contributed directly to the successful implementation of follow-on test campaigns with numerous artificial ice-shape configurations for this 8.9 percent scale model.
Publication Date: Jul 01, 2017
Document ID:
20170007830
(Acquired Aug 23, 2017)
Subject Category: AERONAUTICS (GENERAL)
Report/Patent Number: NASA/TM-2017-219533, AIAA Paper 3017-4327, E-19389, GRC-E-DAA-TN44091
Document Type: Technical Report
Publication Information: (SEE 20170007300; 20170005786)
Contract/Grant/Task Num: WBS 081876.02.03.08.02.02
Financial Sponsor: NASA Glenn Research Center; Cleveland, OH United States
Organization Source: NASA Glenn Research Center; Cleveland, OH United States
Description: 46p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: AERODYNAMICS; AIRCRAFT ICING; LOW REYNOLDS NUMBER; SWEPT WINGS; SEMISPAN MODELS; COMPUTATIONAL FLUID DYNAMICS; MACH NUMBER; TURBULENCE MODELS; SURFACE ROUGHNESS; AERODYNAMIC CONFIGURATIONS; THREE DIMENSIONAL MODELS; WIND TUNNEL TESTS; COMPUTERIZED SIMULATION; LEADING EDGES; RESEARCH AIRCRAFT
Other Descriptors: AIRCRAFT ICING; AERODYNAMICS; SCALE MODELS
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