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Wing configuration

About: Wing configuration is a research topic. Over the lifetime, 1586 publications have been published within this topic receiving 16131 citations.


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Journal ArticleDOI
TL;DR: In this paper, a theory for flight-dynamic analysis of highly flexible flying-wing configurations is presented, which takes into account large aircraft motion coupled with geometrically nonlinear structural deformation subject only to a restriction to small strain.
Abstract: The paper presents a theory for flight-dynamic analysis of highly flexible flying-wing configurations. The analysis takes into account large aircraft motion coupled with geometrically nonlinear structural deformation subject only to a restriction to small strain. A large motion aerodynamic loads model is integrated into the analysis. The analysis can be used for complete aircraft analysis including trim, stability analysis linearized about the trimmed-state, and nonlinear simulation. Results are generated for a typical high-aspect-ratio "flying-wing" configuration. The results indicate that the aircraft undergoes large deformation during trim. The flight-dynamic characteristics of the deformed aircraft are completely different as compared with a rigid aircraft. When the example aircraft is loaded sufficiently, the pair of complex-conjugate short-period roots merges to become two real roots, and the phugoid mode goes unstable. Furthermore, nonlinear flight simulation of the aircraft indicates that the phugoid instability leads to catastrophic consequences.

325 citations

Proceedings ArticleDOI
10 Jul 2017
TL;DR: In this paper, the authors present a summary of the aircraft system studies, technology development, and facility development for a single-aisle aircraft with a tube and wing, partially turbo electric configuration (STARC-ABL).
Abstract: NASA is investing in Electrified Aircraft Propulsion (EAP) research as part of the portfolio to improve the fuel efficiency, emissions, and noise levels in commercial transport aircraft. Turboelectric, partially turboelectric, and hybrid electric propulsion systems are the primary EAP configurations being evaluated for regional jet and larger aircraft. The goal is to show that one or more viable EAP concepts exist for narrow body aircraft and mature tall-pole technologies related to those concepts. A summary of the aircraft system studies, technology development, and facility development is provided. The leading concept for mid-term (2035) introduction of EAP for a single aisle aircraft is a tube and wing, partially turbo electric configuration (STARC-ABL), however other viable configurations exist. Investments are being made to raise the TRL level of light weight, high efficiency motors, generators, and electrical power distribution systems as well as to define the optimal turbine and boundary layer ingestion systems for a mid-term tube and wing configuration. An electric aircraft power system test facility (NEAT) is under construction at NASA Glenn and an electric aircraft control system test facility (HEIST) is under construction at NASA Armstrong. The correct building blocks are in place to have a viable, large plane EAP configuration tested by 2025 leading to entry into service in 2035 if the community chooses to pursue that goal.

199 citations

Journal ArticleDOI
TL;DR: In this paper, a two-dimensional numerical study is applied to simulate the flow-structure interaction of a flapping wing during hovering flight, where the wing section is modeled as an elastic plate, which may experience nonlinear deformations while flapping.
Abstract: Insect wings in flight typically deform under the combined aerodynamic force and wing inertia; whichever is dominant depends on the mass ratio defined as m∗=ρsh/(ρfc), where ρsh is the surface density of the wing, ρf is the density of the air, and c is the characteristic length of the wing To study the differences that the wing inertia makes in the aerodynamic performance of the deformable wing, a two-dimensional numerical study is applied to simulate the flow-structure interaction of a flapping wing during hovering flight The wing section is modeled as an elastic plate, which may experience nonlinear deformations while flapping The effect of the wing inertia on lift production, drag resistance, and power consumption is studied for a range of wing rigidity It is found that both inertia-induced deformation and flow-induced deformation can enhance lift of the wing However, the flow-induced deformation, which corresponds to the low-mass wing, produces less drag and leads to higher aerodynamic power effi

167 citations

Journal ArticleDOI
TL;DR: In this article, the authors performed a systematic fluid-structure interaction based analysis on the aerodynamic performance of a hovering hawkmoth, Manduca, with an integrated computational model of a rigid and flexible wing.
Abstract: Insect wings are deformable structures that change shape passively and dynamically owing to inertial and aerodynamic forces during flight. It is still unclear how the three-dimensional and passive change of wing kinematics owing to inherent wing flexibility contributes to unsteady aerodynamics and energetics in insect flapping flight. Here, we perform a systematic fluid-structure interaction based analysis on the aerodynamic performance of a hovering hawkmoth, Manduca, with an integrated computational model of a hovering insect with rigid and flexible wings. Aerodynamic performance of flapping wings with passive deformation or prescribed deformation is evaluated in terms of aerodynamic force, power and efficiency. Our results reveal that wing flexibility can increase downwash in wake and hence aerodynamic force: first, a dynamic wing bending is observed, which delays the breakdown of leading edge vortex near the wing tip, responsible for augmenting the aerodynamic force-production; second, a combination of the dynamic change of wing bending and twist favourably modifies the wing kinematics in the distal area, which leads to the aerodynamic force enhancement immediately before stroke reversal. Moreover, an increase in hovering efficiency of the flexible wing is achieved as a result of the wing twist. An extensive study of wing stiffness effect on aerodynamic performance is further conducted through a tuning of Young's modulus and thickness, indicating that insect wing structures may be optimized not only in terms of aerodynamic performance but also dependent on many factors, such as the wing strength, the circulation capability of wing veins and the control of wing movements.

155 citations

Journal ArticleDOI
TL;DR: In this article, the aerodynamic characteristics of the variable-span morphing wing are investigated, and a static aero-elastic analysis is performed, which requires not only aerodynamic analysis but also an investigation of the aeroelastic properties of the wing.
Abstract: The morphing concept for unmanned aerial vehicles is a topic of current research interest in aerospace engineering. One concept of morphing is to change the wing configuration during flight to allow for multiple flight regimes. A particular approach to planform morphing is a variable-span morphing wing to increase wingspan to reduce induced drag and increase range and endurance. The wing area and the aspect ratio of the variable-span morphing wing increase as the wingspan increases. This means that the total lift increases while the induced drag is reduced, whereas the wing-root bending moment increases, thus, requiring a larger bending stiffness of the wing structure. Therefore, a study of the variable-span morphing wing requires not only aerodynamic analysis but also an investigation of the aeroelastic characteristics of the wing. The aerodynamic characteristics of the variable-span morphing wing are investigated, and a static aeroelastic analysis is performed.

135 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202323
202255
202131
202040
201948
201857