Numerical Simulation of a High-Aspect-Ratio Wing Using High Fidelity Aero-Structural Coupled Method

2013 ◽  
Vol 465-466 ◽  
pp. 352-357
Author(s):  
Ze Hai Wang ◽  
Ming Yun Lv ◽  
Jun Hui Meng ◽  
Guo Quan Tao
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Aerodynamic Force ◽  
Geometrical Nonlinearity ◽  
High Fidelity ◽  
Coupled Method ◽  
Design And Optimization ◽  
Rigid Model ◽  
Inherent Nature ◽  
Drag Ratio

High-aspect-ratio wings, with the inherent nature of maximizing the lift-to-drag ratio, have been widely employed in modern airplanes. However, highly flexibility wing structure renders previous rigid model in aerodynamic simulation and ideal aerodynamic force distribution in structural simulation meet serious challenges. In this article, a high fidelity aero-structural coupled method is employed to better evaluating the deformation of a high-aspect-ratio wing. Summarily, this method takes into consideration the aerodynamic redistribution and the geometrical nonlinearity caused by large deformation of the wing, and the deflection calculated using coupled method is approximately 20% more than traditional unidirectional method, providing a more accurate model for structural design and optimization.

FE-Modal Approach to Model Geometric Nonlinearities of High Aspect Ratio Wing

2013 ◽  
Vol 390 ◽  
pp. 28-32 ◽  
Author(s):  
Kamran Ahmad ◽  
Zhi Gang Wu ◽  
Hassan Junaid Hasham
Keyword(s):  
Aspect Ratio ◽  
Time Domain ◽  
High Aspect Ratio ◽  
Geometrical Nonlinearity ◽  
External Input ◽  
Rational Fraction ◽  
Domain Modeling ◽  
Modal Approach ◽  
Reduced Frequency ◽  
Time Domain Modeling

Geometrical nonlinearity of high aspect ratio wing arises from the tip deflection which has been modeled through combined FE/modal approach. Generalized aerodynamics forces are obtained through commercial aeroelastic package. In time domain modeling, reduced frequency dependency of the aerodynamics need to be accounted. For state space time domain models this can be done through rational fraction approximation (RFA) of aerodynamics. Karpels minimum state approximation has been used in this work. Linear and nonlinear aeroservoelastic analyses of a high aspect ratio wing have been presented. Only stability and flutter issues are considered in this work while no external input has been considered.

Replica Molding of High-Aspect-Ratio Polymeric Nanopillar Arrays with High Fidelity

Langmuir ◽  
2006 ◽  
Vol 22 (20) ◽  
pp. 8595-8601 ◽  
Author(s):  
Ying Zhang ◽  
Chi-Wei Lo ◽  
J. Ashley Taylor ◽  
Shu Yang
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
High Fidelity ◽  
Replica Molding ◽  
Nanopillar Arrays

scholarly journals A Novel Aerodynamic Force and Flutter of the High-Aspect-Ratio Cantilever Plate in Subsonic Flow

2020 ◽  
Vol 2020 ◽  
pp. 1-17
Author(s):  
Li Ma ◽  
Minghui Yao ◽  
Wei Zhang ◽  
Kai Lou ◽  
Dongxing Cao ◽  
...  
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Subsonic Flow ◽  
Aerodynamic Force ◽  
Limit Cycle Oscillation ◽  
Cantilever Plate ◽  
Dynamical Equations ◽  
Ansys Fluent ◽  
Cycle Oscillation ◽  
Geometric Relationship

This paper focuses on the derivation of the aerodynamic force for the cantilever plate in subsonic flow. For the first time, a new analytical expression of the quasi-steady aerodynamic force related to the velocity and the deformation for the high-aspect-ratio cantilever plate in subsonic flow is derived by utilizing the subsonic thin airfoil theory and Kutta-Joukowski theory. Results show that aerodynamic force distribution obtained theoretically is consistent with that calculated by ANSYS FLUENT. Based on the first-order shear deformation and von Karman nonlinear geometric relationship, nonlinear partial differential dynamical equations of the high-aspect-ratio plate subjected to the aerodynamic force are established by using Hamilton’s principle. Galerkin approach is applied to discretize the governing equations to ordinary differential equations. Numerical simulation is utilized to investigate the relation between the critical flutter velocity and some parameters of the system. Results show that when the inflow velocity reaches the critical value, limit cycle oscillation occurs. The aspect ratio, the thickness, and the air damping have significant impact on the critical flutter velocity of the thin plate.

The Research on Aeroelasticity of the Vehicle Wing Surface

2011 ◽  
Vol 284-286 ◽  
pp. 2456-2460
Author(s):  
Zhi Ling Peng
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Aerodynamic Force ◽  
Wing Surface ◽  
Flutter Speed ◽  
Straight Wing

By taking high aspect ratio straight wing as the research object, static aerodynamic force and dynamic aerodynamic force are detailed analysed and researched. The flutter speed of panel derived from Unsteady Theory and Theory.

scholarly journals Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation

2017 ◽  
Vol 2017 ◽  
pp. 1-16
Author(s):  
Changchuan Xie ◽  
Yang Meng ◽  
Fei Wang ◽  
Zhiqiang Wan
Keyword(s):  
Aspect Ratio ◽  
Large Deformation ◽  
High Aspect Ratio ◽  
Optimization Design ◽  
Geometrical Nonlinearity ◽  
Computing Time ◽  
Wind Tunnel Test ◽  
Lattice Method ◽  
Wing Model ◽  
Design Variables

This paper presents a framework of aeroelastic optimization design for high-aspect-ratio wing with large deformation. A highly flexible wing model for wind tunnel test is optimized subjected to multiple aeroelastic constraints. Static aeroelastic analysis is carried out for the beamlike wing model, using a geometrically nonlinear beam formulation coupled with the nonplanar vortex lattice method. The flutter solutions are obtained using the P-K method based on the static equilibrium configuration. The corresponding unsteady aerodynamic forces are calculated by nonplanar doublet-lattice method. This paper obtains linear and nonlinear aeroelastic optimum results, respectively, by the ISIGHT optimization platform. In this optimization problem, parameters of beam cross section are chosen as the design variables to satisfy the displacement, flutter, and strength requirements, while minimizing wing weight. The results indicate that it is necessary to consider geometrical nonlinearity in aeroelastic optimization design. In addition, optimization strategies are explored to simplify the complex optimization process and reduce the computing time. Different criterion values are selected and studied for judging the effects of the simplified method on the computing time and the accuracy of results. In this way, the computing time is reduced by more than 30% on the premise of ensuring the accuracy.

Numerical analysis of geometrical nonlinear aeroelasticity with CFD/CSD method

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Xueyuan Nie
Keyword(s):  
Finite Element ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Data Transfer ◽  
Geometrical Nonlinearity ◽  
Three Dimensional ◽  
Geometrical Nonlinear ◽  
Static Aeroelasticity ◽  
Nonlinear Static ◽  
Linear And Nonlinear

Abstract A nonlinear static aeroelastic methodology based on the coupled CFD/CSD approach has been developed to study the geometrical nonlinear aeroelastic behaviors of high-aspect-ratio or multi-material flexible aerial vehicles under aerodynamic loads. The Reynolds-averaged Navier–Stokes solver combined with the three-dimensional finite-element nonlinear solver is used to perform the fluid-structure coupling simulation. The interpolation technique for data transfer between the aerodynamic and structural modules employs radial basis function algorithm as well as dynamic mesh deformation. A high-aspect-ratio structure with multi-material is modeled by the finite element method to investigate the effects of geometrical nonlinearity on the aeroelastic behavior. Numerical simulations of the linear and nonlinear static aeroelasticity were conducted at transonic regime with different angles of attack. By comparing the aeroelastic behaviors of linear and nonlinear structure, it shows that geometrical nonlinearity plays an important role for flexible high-aspect-ratio wings undergoing the large static aeroelastic deformation and should be taken into account in aeroelastic analysis for such structures.

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