Method for Designing Three-Dimensional Swept Hybrid Wings for Icing Wind-Tunnel Tests

Fujiwara, Gustavo E. C.; Bragg, Michael B.

doi:10.2514/1.c035136

Cited by 12 publications

(5 citation statements)

References 33 publications

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“…The greater the η value, the greater the influence of icing on aerodynamic parameters. The meteorological factor is about 0-0.3. k C(A) is the icing factor of aircraft, which is a fixed value for a specific aircraft, usually obtained by test or flight simulation calculation [23], [24].…”

Section: Icing Effect Modelmentioning

confidence: 99%

On Flight Risk Analysis Method Based on Stability Region of Dynamic System Under Icing Conditions

Duan

et al. 2020

IEEE Access

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The occurrence of loss of control in flight is often accompanied by deep coupling of flight parameters. In order to explore the mechanism of coupling induced flight risk, a method of flight risk assessment based on the stability region of a nonlinear dynamic system was proposed. The Monte Carlo method was improved to identify the boundary of the stability region, and the key parameters that can represent the flight safety were set. The risk quantification method and the colorized flight risk characterization method were proposed. Combined with the case of aircraft encountering icing, the variation trend of flight stability region and flight risk under different icing degrees was calculated. The results showed that with the aggravation of icing, the flight stability region was significantly reduced and the coupling of flight parameters was aggravated. And compared with the traditional angle of attack protection method, this method can find the potential flight risk earlier, and characterize the way of parameters' coupling and the flight risk evolution process. The proposed method can improve the pilot's situational awareness, and also provide theoretical support for the prevention of flight risk under adverse conditions, and provide reference for the further development of boundary protection control law. INDEX TERMS Flight risk, quantitative assessment, stability region, ice encountering, risk visualization.

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Section: Icing Effect Modelmentioning

confidence: 99%

On Flight Risk Analysis Method Based on Stability Region of Dynamic System Under Icing Conditions

Duan

et al. 2020

IEEE Access

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“…The IRT simulations incorporate the models in the IRT. Fujiwara et al [14][15][16][17][18] describe the design of these models in detail in several publications, and Broeren et al [7] explain the experimental setup in the IRT. The IRT models have full-scale leading edges that match a single slice from the CRM65.…”

Section: Artificial Ice-shape Configurationsmentioning

confidence: 99%

“…For this project, the full-scale geometry is a 65% scale version of the CRM, designated here as CRM65 [1]. The design of the icing tunnel models is described by Fujiwara et al in several publications [14][15][16][17][18]. Low-Reynolds number testing was performed using an 8.9% scale model of the CRM65, and the high-Reynolds number testing utilized a 13.3% scale model.…”

mentioning

confidence: 99%

Experimental Aerodynamic Simulation of a Scallop Ice Accretion on a Swept Wing

Woodard¹,

Broeren²,

Potapczuk³

et al. 2019

SAE Int. J. Adv. & Curr. Prac. in Mobility

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Understanding the aerodynamic impact of swept-wing ice accretions is a crucial component of the design of modern aircraft. Computersimulation 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. 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 = 11.9×10 6 . Past work focused on only three different fidelity variations for ice shapes based on multiple icing conditions. This work presents a more detailed investigation into several fidelity representations of a single highly three-dimensional scallop ice accretion. Sensitivity to roughness size and application technique on a low-fidelity smooth ice shape is described. The data indicate that the aerodynamic performance is not especially sensitive to the grit variations. An ice accretion code was also used to generate ice shapes for aerodynamic testing and comparisons. These ice shapes have a general appearance like the low-fidelity smooth ice shapes, but in this case, the computer-generated ice shape is significantly smaller. As such, the impact of that ice shape on the aerodynamic performance of the wing is reduced compared to the smooth ice shape based on the icing experiment for those same conditions. Spanwise discontinuities were also introduced to a lowfidelity ice shape in an attempt to quantify the impact of those variation in the high-fidelity ice shape. While the lift data indicate good agreement between the high-fidelity ice shapes and the lowfidelity ice shapes with spanwise discontinuities, a closer investigation of the data suggests potential, significant differences in the flowfield. These results were similar at both facilities over the wide range of test conditions utilized.10/19/2016 developing these artificial ice shapes [8]. During that project, the current methods for capturing three-dimensional geometries were not available, but more recently a method for creating high-fidelity artificial ice shapes has been validated using 3-D laser scanning and rapid-prototype manufacturing [9]. That methodology was utilized for this project. With these capabilities applied to the swept-wing ice accretion database, numerous artificial ice shapes are available for wind tunnel testing for aerodynamic performance effects. Both lowand high-Reynolds...

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“…Theoretically, we can obtain the most accurate experimental results if a full-scale model is used for icing tests. However, icing wind tunnels are too small to test full-scale airfoils or wings; even for a moderate-or small-sized model, it may cause tunnel blockage [4] or wind tunnel wall interference when the model's angle of attack (AoA) is adjusted. To weaken the blockage and acquire ice characteristics of the full-scale model under existing conditions, scaled model is used to substitute the full-scale model.…”

Section: Introductionmentioning

confidence: 99%

A Parametric Design Method for Hybrid Airfoils for Icing Wind Tunnel Test

Yang

Tong

et al. 2021

International Journal of Aerospace Engineering

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The size of aircraft models that can be tested in icing wind tunnels is limited by the dimensions of the facilities in present; it is an effective method to replace the large model with a hybrid airfoil to carry out the experiment. A design method of multiple control points for hybrid airfoil based on the similarity of flow field in the leading edge of airfoil is proposed. Aiming at generating the full-scale flow field and ice accretion on the leading edge, multiobjective genetic optimization algorithm is used to design the hybrid airfoil under different conditions by combining the airfoil parameterization and solution of spatial constraint. Pressure tests of hybrid airfoils are carried out and compared with the leading edge pressure of the corresponding full-scale airfoils. The design and experimental results show that the pressure coefficient deviation between the hybrid airfoils designed and the corresponding full-scale airfoil in the 15% chord length range of the leading edge is within 4%. Finally, the vortex distribution and ice accretion process of the two airfoils were simulated by the unsteady Reynolds-averaged-Navier–Stokes (URANS) equations and multistep ice numerical method; it is shown that the hybrid airfoil can provide the same vortex distribution and ice accretion with the full-scale airfoil.

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Method for Designing Three-Dimensional Swept Hybrid Wings for Icing Wind-Tunnel Tests

Cited by 12 publications

References 33 publications

On Flight Risk Analysis Method Based on Stability Region of Dynamic System Under Icing Conditions

On Flight Risk Analysis Method Based on Stability Region of Dynamic System Under Icing Conditions

Experimental Aerodynamic Simulation of a Scallop Ice Accretion on a Swept Wing

A Parametric Design Method for Hybrid Airfoils for Icing Wind Tunnel Test

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