Numerical Study of Camber Morphing in NACA0012 Airfoil
15 Jun 2020-
About: The article was published on 2020-06-15. It has received 3 citations till now. The article focuses on the topics: Camber (aerodynamics) & Airfoil.
Citations
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TL;DR: In this article, an iterative scheme for geometrically large deflection analysis of corrugated structures using the nonlinear shooting method is proposed, which is extended to various boundary conditions (fixed-fixed and fixed-hinged) and loading conditions (point loads and uniformly distributed load).
Abstract: This manuscript proposes an iterative scheme for geometrically large deflection analysis of corrugated structures using the nonlinear shooting method. The corrugated structure is modeled by discretizing it in several corrugated units. The solution of each unit is obtained assuming it to be consistering of several beam elements. Finally, the deflection of a corrugated structure is calculated assembling the deflection of each of the corrugated units. The formulation has been extended to various boundary conditions (fixed–fixed and fixed–hinged) and loading conditions (point loads and uniformly distributed load). This shows the versatility of the methods in solving various problems. Furthermore, two prototypes of the corrugated structure are fabricated using aluminum and carbon fiber reinforced polymer (CFRP) laminate, and a moment actuation test is performed. The deflections of these prototypes obtained using the proposed iterative scheme are compared with the numerical model and validated with experiments, and results are found to be in good agreement.
6 citations
TL;DR: In this paper, an iterative scheme for the large deflection analysis of double corrugated cantilever structures subjected to end point loads and uniformly varying load using a chain algorithm is proposed.
2 citations
08 Jun 2023
TL;DR: In this paper , a wing design with a morphing trailing edge is presented, which is easy to manufacture and control while allowing the execution of appropriate aerodynamic studies in wind tunnel.
Abstract: In recent years, the interest in morphing technologies has been continuously growing. Many designs have been developed, but some are very complex to manufacture. The main goal of this paper is to present a wing design with a morphing trailing edge that is easy to manufacture and control while allowing the execution of appropriate aerodynamic studies in wind tunnel. Using computer-aided design and 3D printing, a wing that is easily controlled with easy-to-use hardware is developed, manufactured, and studied using flow visualization and force acquisition. Flow visualization showed that the presence of curvature delays stall occurrence when compared to the symmetrical configuration, where flow separation starts right at the leading edge. This is validated by force measurements where curvature plays an important role regarding lift enhancement. This design will allow for a wider range of studies, including unsteady conditions, which can offer insights concerning aerodynamic surfaces design.
References
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TL;DR: In this paper, two new two-equation eddy-viscosity turbulence models are presented, which combine different elements of existing models that are considered superior to their alternatives.
Abstract: Two new two-equation eddy-viscosity turbulence models will be presented. They combine different elements of existing models that are considered superior to their alternatives. The first model, referred to as the baseline (BSL) model, utilizes the original k-ω model of Wilcox in the inner region of the boundary layer and switches to the standard k-e model in the outer region and in free shear flows. It has a performance similar to the Wilcox model, but avoids that model's strong freestream sensitivity
15,459 citations
01 Jan 1989
TL;DR: In this article, an inviscid linear-vorticity panel method with a Karman-Tsien compressiblity correction is developed for direct and mixed-inverse modes.
Abstract: Calculation procedures for viscous/inviscid analysis and mixed-inverse design of subcritical airfoils are presented. An inviscid linear-vorticity panel method with a Karman-Tsien compressiblity correction is developed for direct and mixed-inverse modes. Source distributions superimposed on the airfoil and wake permit modeling of viscous layer influence on the potential flow. A two-equation lagged dissipation integral method is used to represent the viscous layers. Both laminar and turbulent layers are treated, with an e 9-type amplification formulation determinining the transition point. The boundary layer and transition equations are solved simultaneously with the inviscid flowfield by a global Newton method. The procedure is especially suitable for rapid analysis of low Reynolds number airfoil flows with transitional separation bubbles. Surface pressure distributions and entire polars are calculated and compared with experimental data. Design procedure examples are also presented.
2,185 citations
TL;DR: In this paper, the authors classify the shape morphing parameters that can be affected by planform alteration (span, sweep, and chord), out-of-plane transformation (twist, dihedral/gull, and span-wise bending), and airfoil adjustment (camber and thickness).
Abstract: Aircraft wings are a compromise that allows the aircraft to fly at a range of flight conditions, but the performance at each condition is sub-optimal. The ability of a wing surface to change its geometry during flight has interested researchers and designers over the years as this reduces the design compromises required. Morphing is the short form for metamorphose; however, there is neither an exact definition nor an agreement between the researchers about the type or the extent of the geometrical changes necessary to qualify an aircraft for the title ‘shape morphing.’ Geometrical parameters that can be affected by morphing solutions can be categorized into: planform alteration (span, sweep, and chord), out-of-plane transformation (twist, dihedral/gull, and span-wise bending), and airfoil adjustment (camber and thickness). Changing the wing shape or geometry is not new. Historically, morphing solutions always led to penalties in terms of cost, complexity, or weight, although in certain circumstances, thes...
1,068 citations
TL;DR: In this article, a method of accurately calculating transonic and low Reynolds number airfoil flows, implemented in the viscous-inviscid design/analysis code ISES, is presented.
Abstract: A method of accurately calculating transonic and low Reynolds number airfoil flows, implemented in the viscous-inviscid design/analysis code ISES, is presented. The Euler equations are discretized on a conservative streamline grid and are strongly coupled to a two-equation integral boundary-layer formulation, using the displacement thickness concept. A transition prediction formulation of the e type is derived and incorporated into the viscous formulation. The entire discrete equation set, including the viscous and transition formulations, is solved as a fully coupled nonlinear system by a global Newton method. This is a rapid and reliable method for dealing with strong viscous-inviscid interactions, which invariably occur in transonic and low Reynolds number airfoil flows. The results presented demonstrate the ability of the ISES code to predict transitioning separation bubbles and their associated losses. The rapid airfoil performance degradation with decreasing Reynolds number is thus accurately predicted. Also presented is a transonic airfoil calculation involving shock-induced separation, showing the robustness of the global Newton solution procedure. Good agreement with experiment is obtained, further demonstrating the performance of the present integral boundary-layer formulation.
1,042 citations
TL;DR: Early morphing aircraft history is reviewed to identify inventions and innovations that led to both successes and failures, and recent government-sponsored activities in the United States are discussed.
Abstract: The term ‘morphing aircraft’ describes a broad range of air vehicles and vehicle components that adapt to planned and unplanned multipoint mission requirements. Adaptation or morphing requires changing system features including vehicle ‘states,’ such as vehicle shape, during in-flight operation. The term morphing can be applied to almost any activity in which in-flight vehicle features are changed. As such, morphing has become a buzzword loosely applied to a wide variety of activities, some of which are disconnected from air vehicle morphing development. This has led to three myths: 1) morphing shape change is too expensive, 2) morphing aircraft must weigh more than nonmorphing aircraft, and 3) morphing requires exotic materials and complex systems. This paper attempts to dispel these myths by reviewing early morphing aircraft history to identify inventions and innovations that led to both successes and failures. The review also discusses recent government-sponsored activities in the United States: in par...
291 citations