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Title Design of 3D swept wing hybrid models for icing wind tunnel tests
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Publication Date
Date Accessioned
Degree MS
Discipline/Department 4048
Degree Level thesis
University/Publisher University of Illinois – Urbana-Champaign
Abstract The study of aircraft icing is critical to ensure the safety of any aircraft that might experience icing conditions in flight, including general, commercial, and military aviation. The certification of modern commercial transports requires manufacturers to demonstrate that these aircraft can safely operate during icing conditions through a set of flight tests, consistent with the standards set forth by the Federal Aviation Administration. This is often expensive and challenging to find the appropriate icing test conditions. Thus, both computational methods and icing wind tunnel experiments are utilized during the design and certification of aircraft ice-protection systems to provide a controlled and repeatable environment to mitigate risks, reduce costs, and validate the existing computational icing tools. However, the existing icing wind tunnel facilities cannot accommodate large wings such as those found on modern commercial aircraft without being dramatically scaled. Two methods of scaling exist. The first geometrically scales the entire geometry to fit inside the tunnel test section and then scales the icing conditions to obtain icing similitude. The second maintains the full-scale leading edge of the reference geometry and replaces the aft section with a truncated trailing edge that produces a similar flowfield around the leading edge with a significantly shorter chord, reducing model size and tunnel blockage. This type of model is referred to as a hybrid and its biggest advantage lies in the fact that it is designed to produce full-scale ice shapes, while reducing or even eliminating the need for icing scaling. While a design method for a straight, untapered hybrid wing is well documented and there is a broad set of experimental data available, the design of a swept, hybrid wing lacks both a design method and experimental data. This thesis established a design method for large hybrid swept wings that reproduce full-scale ice accretions through icing wind tunnel tests. The design method was broken down in two steps: 1) A 2D hybrid airfoil design, and 2) A 3D hybrid swept wing design. Multiple existing computational tools were employed and several parametric studies performed. It was shown, in 2D, that matching the stagnation point location on the leading edge of the hybrid airfoil had a first-order impact on matching the full-scale ice shape, while matching the suction peak magnitude and location had a second-order effect. The closer to the leading edge lift was generated for a given hybrid design, the less total load was required to reach the same stagnation point location. As an implication, more front-loaded airfoils required less lift than more aft-loaded ones to reach the same stagnation point location on a hybrid airfoil. More front load also increased the risk of flow separation near the leading edge, while more aft load increased the risk of separation near the trailing edge. Finally, higher hybrid scale factors were shown to increase the risk of flow separation. In 3D, sweep angle was…
Subjects/Keywords Aerodynamics; aircraft icing; wind tunnel; icing; ice shape; Accretion; hybrid; sweep; swept; wing; computational fluid dynamics (CFD); aircraft certification; wing design
Contributors Bragg, Michael B. (advisor)
Language en
Rights Copyright 2014 Gustavo Eidji Camarinha Fujiwara
Country of Publication us
Record ID handle:2142/72880
Repository uiuc
Date Indexed 2020-03-09
Grantor University of Illinois at Urbana-Champaign
Issued Date 2015-01-21 00:00:00

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wing having a quarter-chord sweep angle of 35◦ . The supercritical wing was designed for a cruise Mach number of M = 0.85. The aircraft body extends to 10% semispan with a Yehudi break at 37% semispan and 8◦ of washout from side-of-body to tip. The full…

…Reynolds Averaged Navier-Stokes SF = Scale Factor SST = Shear Stress Transport TWE = Total Water Exposure UIUC = University of Illinois at Urbana-Champaign WB = Wing/Body xiv Chapter 1 Introduction 1.1 Motivation The study of aircraft icing…

…systems (engines, inlets, flight instruments), affecting aircraft performance and safety. Depending on the location of the ice, the shape of the wing, and the phase of flight, even small, almost imperceptible amounts of ice can have a significant…

…present work intends to give its contribution by further understanding the issues related to swept wing icing. Aircraft Icing Protection Program Icing Avoidance Icing Tolerant Aircraft Engine Icing Straight Wing Icing Icing Atmospheric…

…classification system for ice shapes on 3D swept wings and identified areas where more research is required to fully understand swept wing icing effects. Although wind tunnel testing is crucial to aircraft certification, the existing icing wind tunnel facilities…

…configuration of the Common Research Model: Wing-Body-Nacelle-Pylon-Horizontal Tail 6 Table 1.1: Comparison of the Common Research Model with Existing Wide-Body Aircraft Aircraft Span (ft.) Mean Aerodynamic Chord (ft.) CRM Airbus A330…

…performing such testing for aircraft certification as well as considering the ability of CFD to accurately model ice accretion in this environment. 1.4 Objective The objective of this research is to establish a hybrid wing design method for large swept…

…CRM65) as the baseline model for the project, in Figure 2.1. Figure 2.1: CRM65 geometry: Wing-Body 8 The CRM65 has a semispan of b/2 = 751.89 in. (19.10 m), a quarter-chord sweep of Λ = 35 ◦ , aspect ratio of AR = 9.0, taper ratio of λ…

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