Modeling and Simulation of Unsteady Aerodynamics on a Morphing Wing

2013 ◽  
Vol 427-429 ◽  
pp. 77-80 ◽  
Author(s):  
Zhi Gang Wang ◽  
Zhen Ning Zhang
Keyword(s):  
Modeling And Simulation ◽  
Unsteady Aerodynamics ◽  
Simulation Method ◽  
Computer Code ◽  
Morphing Wing ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Induced Drag ◽  
Morphing Wings ◽  
Time Histories

Modeling and simulation method of unsteady aerodynamics on morphing wings were investigated. The Unsteady Vortex Lattice Method is employed to model the unsteady aerodynamics of 3-D potential flow field surrounding the wing. An UVLM computer code was then developed and validated for numerical simulation. A morphing wing which changes its dihedral angle with constant angular velocity was investigated by the code, and the lift, induced drag, and pitching moment coefficients time histories were obtained. The results show that the UVLM code is an effective tool for simulations of unsteady aerodynamics on morphing wings.

Unsteady aerodynamics investigation of deploying tandem-wing with different methods

2018 ◽  
Vol 233 (10) ◽  
pp. 3714-3733 ◽  
Author(s):  
Hao Cheng ◽  
Hua Wang ◽  
Qingli Shi ◽  
Mengying Zhang
Keyword(s):  
Fore Wing ◽  
Vortex Lattice ◽  
Lift Coefficient ◽  
Unsteady Aerodynamics ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Induced Drag ◽  
Lifting Line ◽  
Lifting Line Method ◽  
Unsteady Lift

In the rapidly deploying process of the unmanned aerial vehicle with folding wings, the aerodynamic characteristics could be largely different owing to the effects of deformation rate and the aerodynamic interference. The investigation on the unsteady aerodynamics is of great significance for the stability analysis and control design. The lifting-line method and the vortex-lattice method are improved to calculate the unsteady aerodynamics in the morphing stage. It is validated that the vortex-lattice method predicts the unsteady lift coefficient more appropriately than the lifting-line method. Different tandem wing configurations with deployable wings are simulated with different deformation rates during the morphing stage by the vortex-lattice method. As results indicated, the unsteady lift coefficient and the induced drag of the fore wing rise with the deformation rate increasing, but it is reversed for the hind wing. Additionally, the unsteady lift coefficient of the tandem wing configuration performs well with a larger stagger, a larger magnitude of the gap and a larger wingspan of the fore wing; however, the total induced drag has a larger value for the configuration that the two lifting surfaces with the same wingspans are closer to each other.

scholarly journals Induced Drag Calculations with the Unsteady Vortex Lattice Method for Cambered Wings

AIAA Journal ◽  
2017 ◽  
Vol 55 (2) ◽  
pp. 668-672 ◽  
Author(s):  
Thomas Lambert ◽  
Grigorios Dimitriadis
Keyword(s):  
Vortex Lattice ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Induced Drag

scholarly journals Unsteady Aerodynamics of Highly Maneuvering Flyers

2021 ◽  
Author(s):  
Mohamed Yehia Zakaria
Keyword(s):  
Unsteady Aerodynamics ◽  
Leading Edge ◽  
High Amplitude ◽  
Analytical Models ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Classical Models ◽  
Zero Degree ◽  
Edge Vortex ◽  
Unsteady Lift

In this chapter, a set of analytical aerodynamic models, based on potential flow, that can be used to predict the unsteady lift response during pitching maneuvers are presented and assessed. The result examines the unsteady lift coefficients experienced by a flat plate in high-amplitude pitch ramp motion. The pitch ramps are chosen based on two ramp pitch maneuvers of a maximum amplitudes of 25 and 45 degrees starting from zero degree. The aim is investigate the use of such classical models in predicting the lift dynamics compared to a full physical-based model. Among all classical methods used, the unsteady vortex lattice method (without considering the leading edge vortex) is found to be a very good predictor of the motion lift dynamic response for the 25° ramp angle case. However, at high pitch maneuvers (i.e.,the 45° ramp angle case), could preserve the response pattern with attenuated amplitudes without high computational burden. These mathematical analytical models presented in this chapter can be used to obtain a fast estimate for aircraft unsteady lift during pitch maneuvers instead of high fidelity models, especially in the early design phases.

Numerical Approach to Aeroelastic Responses of Three-Dimensional Flexible Sails

1993 ◽  
Author(s):  
Toichi Fukasawa ◽  
Masanobu Katori
Keyword(s):  
Numerical Simulations ◽  
Vortex Lattice ◽  
Three Dimensional ◽  
Numerical Approach ◽  
The Finite Element Method ◽  
Lattice Method ◽  
3 Dimensional ◽  
Vortex Lattice Method ◽  
Induced Drag ◽  
Displacement Theory

Aeroelastic responses of 3-dimensional flexible sails are investigated by means of numerical simulations. An incremental finite displacement theory using the Finite Element Method is adopted to describe the structural behavior of the sail. A modified Vortex Lattice Method is used to calculate the aerodynamic pressures on the sail. Combining these two methods, the structural and aerodynamic responses of the sail are solved simultaneously. Numerical simulations are performed for actual 3- dimensional sails. Deformations and stresses of the sail in steady flow are calculated. Unsteady sail dynamics are also investigated in the case where the sailing vessel is pitching and rolling in a seaway. The effects of the flexibility of the sail upon the lift, induced drag and the center of effort are clarified.

Application of Vortex Lattice Method and Surface Spline Function in Terrain-Induced Wind Field

2013 ◽  
Vol 444-445 ◽  
pp. 574-578
Author(s):  
Chu Tang ◽  
Guan Xin Hong
Keyword(s):  
Wind Field ◽  
Complex Terrain ◽  
Simulation Method ◽  
Vortex Rings ◽  
Lattice Method ◽  
Linear Superposition ◽  
Vortex Lattice Method ◽  
Surface Spline ◽  
Induced Velocity ◽  
Singularity Distribution

A numerical simulation method for the wind field over complex terrain is developed in this paper. The complex terrain is represented by a surface, which is established by the surface spline method basing on the contour line of the map. Then it is divided into panels containing vortex ring singularities. The singularity distribution is solved by combining with the potential flow theory and the boundary condition of terrain surface. Finally, the wind field is simulated by linear superposition of the uniform stream and the induced velocity of vortex rings. A numerical example is studied, and the result indicates that the method proposed in this paper could describe the terrain much more accurately and provide a reasonable result of wind field distribution, but has a simple and efficient procedure, which is suitable for the engineering use in flight dynamics.

scholarly journals Model of a Ducted Axial-Flow Hydrokinetic Turbine – Results of Experimental and Numerical Examination

2018 ◽  
Vol 25 (3) ◽  
pp. 113-122 ◽  
Author(s):  
Adam Góralczyk ◽  
Adam Adamkowski
Keyword(s):  
Vortex Lattice ◽  
Axial Flow ◽  
Computer Code ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Hydrokinetic Turbines ◽  
Hydrokinetic Turbine ◽  
Cavitation Tunnel ◽  
Research Equipment ◽  
Numerical Examination

Abstract The article presents the numerical algorithm of the developed computer code which calculates performance characteristics of ducted axial-flow hydrokinetic turbines. The code makes use of the vortex lattice method (VLM), which has been developed and used in IMP PAN for years, to analyse the operation of various fluid-flow machines. To verify the developed software, a series of model tests have been performed in the cavitation tunnel being part of IMP PAN research equipment.

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