The aeroelastic characteristics of high aspect ratio wing

2016 ◽  
Vol 230 (14) ◽  
pp. 2543-2556
Author(s):  
Fan Yang ◽  
Zhufeng Yue ◽  
Lei Li
Keyword(s):  
Aspect Ratio ◽  
Large Deformation ◽  
High Aspect Ratio ◽  
Data Exchange ◽  
Stokes Equations ◽  
Great Influence ◽  
Aerodynamic Characteristics ◽  
Interface Problem ◽  
Numerical Result ◽  
Computational Structural Mechanics

Owing to the elasticity, the large deformation was brought in the high aspect ratio wing in the flight. The large deformation had a great influence on the flight performance. In this paper, the loosely coupled method was used for the research of high aspect ratio wing aeroelastic problems. The Navier–Stokes equations were solved for fluid domain computation, and the nonlinear finite element method was adopted for solid domain computation. The data exchange program and mesh regeneration progress were adopted for fluid–structure interface problem. Finally, the aerodynamic characteristics of high aspect ratio wing were obtained under different fly conditions. In addition, to validate the proposed method, the flutter analysis of AGARD 445.6 wing is carried out and compared with the experimental data. The numerical result validates the proposed computational fluid dynamics/computational structural mechanics method.

Study of Aerodynamic Characteristics of Cylindrical Bodies in a Supersonic Flow

2011 ◽  
Vol 6 (4) ◽  
pp. 16-24
Author(s):  
Vladimir Kornilov ◽  
Vladimir Lysenko
Keyword(s):  
Mach Number ◽  
Aspect Ratio ◽  
Stokes Equations ◽  
Aerodynamic Force ◽  
Angle Of Attack ◽  
Aerodynamic Characteristics ◽  
Circular Cylinders ◽  
Coordinate Systems ◽  
Flow Parameters ◽  
Cylinder Drag

Analysis of experimental and computational aerodynamic characteristics of smooth flat-face circular cylinders with the aspect ratio of 0,6 to 12,0 is given. Studies have been carried out at Mach number М= 4 for the angle of attack range  = 0900 . Effect of the cylinder aspect ratio and angle of attack on aerodynamic force coefficients in wind axes- and body axes coordinate systems is shown. A number of distinctive peculiarities in the behavior of the cylinder drag coefficient are revealed. The results obtained are presented in a form of a unique generalized dependence. The computation of some flow parameters around a cylinder has been performed within the Navie – Stokes equations, results of which are compared with the flow visualization data

Static Aeroelasticity Analysis of High Aspect Ratio Wing and the Jig-Shape Design Based on Multi-Block Structural Grid

2013 ◽  
Vol 302 ◽  
pp. 377-383 ◽  
Author(s):  
Yan Liu ◽  
Jun Qiang Bai ◽  
Jun Hua
Keyword(s):  
Aspect Ratio ◽  
Design Process ◽  
High Aspect Ratio ◽  
Design Method ◽  
Aerodynamic Characteristics ◽  
Shape Design ◽  
Transport Aircraft ◽  
Mesh Motion ◽  
Static Aeroelasticity ◽  
Motion Method

The influence of structural elastic deformation on the aerodynamic characterisitcs of large transport aircraft has been researched. A method of static aeroelasticity based on multi-block structural grid of high aspect ratio wing has been established, and then a design method of jig-shape is developed. The technology of RBF interpolation is used to exchange the data of CFD/CSD. Based on RBF&Delaunay technology, a mesh motion method is developed to make the design process less time-consuming, which can be applied to large deformation of multi-block structural grid. The static aeroelastic deformation of a wing-body of large transport aircraft is analyzed. Then the wing-body's jig-shape is designed. Compared the aerodynamic characteristics between design cruise shape and target cruise shape, it shows that the aerodynamic characteristics of design cruise shape is almost equal to target cruise shape and the design process of jig-shape is feasible.

Pitching effect on transonic wing stall of a blended flying wing with low aspect ratio

2018 ◽  
Vol 32 (12n13) ◽  
pp. 1840040
Author(s):  
Yang Tao ◽  
Zhongliang Zhao ◽  
Junqiang Wu ◽  
Zhaolin Fan ◽  
Yi Zhang
Keyword(s):  
Shock Wave ◽  
Aspect Ratio ◽  
Stokes Equations ◽  
Vortex Breakdown ◽  
Great Influence ◽  
Second Order ◽  
Upwind Scheme ◽  
Detached Eddy Simulation ◽  
Low Aspect Ratio ◽  
Wing Stall

Numerical simulation of the pitching effect on transonic wing stall of a blended flying wing with low aspect ratio was performed using improved delayed detached eddy simulation (IDDES). To capture the discontinuity caused by shock wave, a second-order upwind scheme with Roe’s flux-difference splitting is introduced into the inviscid flux. The artificial dissipation is also turned off in the region where the upwind scheme is applied. To reveal the pitching effect, the implicit approximate-factorization method with sub-iterations and second-order temporal accuracy is employed to avoid the time integration of the unsteady Navier–Stokes equations solved by finite volume method at Arbitrary Lagrange–Euler (ALE) form. The leading edge vortex (LEV) development and LEV circulation of pitch-up wings at a free-stream Mach number M = 0.9 and a Reynolds number Re = [Formula: see text] is studied. The Q-criterion is used to capture the LEV structure from shear layer. The result shows that a shock wave/vortex interaction is responsible for the vortex breakdown which eventually causes the wing stall. The balance of the vortex strength and axial flow, and the shock strength, is examined to provide an explanation of the sensitivity of the breakdown location. Pitching motion has great influence on shock wave and shock wave/vortex interactions, which can significantly affect the vortex breakdown behavior and wing stall onset of low aspect ratio blended flying wing.

scholarly journals AERO DYNAMIC SHAPE OF TRANSPORT AIRCRAFT “FLYING WING” SCHEME WITH HIGH ASPECT RATIO

2014 ◽  
pp. 84-92
Author(s):  
Олег Львович Лемко ◽  
Євген О. Кушніренко
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Aerodynamic Characteristics ◽  
Design Parameters ◽  
Scientific Methods ◽  
Transport Aircraft ◽  
Research Problems ◽  
And Performance ◽  
Forming Methods ◽  
Dynamic Shape

"Normal" aerodynamic scheme despite the fact that it has become the dominant in global aviation, in terms of aerodynamics is not ideal. To create a lifting force only wing is just necessary. All other elements of aircraft glider - fuselage , horizontal and vertical tail exist only for the crew, passengers and cargo, ensuring the sustainability and management to provide a satisfactory landing characteristics. It became apparent that with the increasing size of the planes becomes possible and appropriate to place all the major part of their weight directly in the wing. This idea was expressed in aerodynamic scheme "flying wing".The purpose of the research is to form aerodynamic look of transport aircraft "flying wing" scheme with high aspect ratio, creating aerodynamic design that provides the greatest rate of return and optimal weight range and flight duration.Objectives of the study are: analysis of scientific sources on establishing LA scheme "flying wing", development of forming methods of the aerodynamic look of transport aircraft scheme "flying wing", based on a synthesis of existing methods for assessing the flight - the technical characteristics of the aircraft, studies and analyzes of theoretical methods of aerodynamic layouts transport aircraft "flying wing" scheme to determine the aerodynamic and flight characteristics.            Were used following scientific methods to solve the research problems:             1. Method of forming the aerodynamic characteristics of the freeform aircraft shape in the parameters of similarity and generalized design parameters.             2. Statistical methods for assessing the aerodynamic and performance characteristics.             3. Numerical methods.The practical value of my work: developed method allows you to create aerodynamic layout scheme aircraft "flying wing" of the great extension that allows you to fully realize the benefits of the scheme, developed and reasonable advices on the aircraft aerodynamic look of "flying wing" scheme of high aspect ratio.

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