scholarly journals Induced-Drag Calculations in the Unsteady Vortex Lattice Method

AIAA Journal ◽  
2013 ◽  
Vol 51 (7) ◽  
pp. 1775-1779 ◽  
Author(s):  
Robert J. S. Simpson ◽  
Rafael Palacios ◽  
Joseba Murua
Keyword(s):  
Vortex Lattice ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Induced Drag

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

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.

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.

Generalized vortex lattice method for planar supersonic flow

AIAA Journal ◽  
1997 ◽  
Vol 35 ◽  
pp. 1230-1233
Author(s):  
Paulo A. O. Soviero ◽  
Hugo B. Resende
Keyword(s):  
Supersonic Flow ◽  
Vortex Lattice ◽  
Lattice Method ◽  
Vortex Lattice Method

scholarly journals Static Aeroelastic Characteristics of Morphing Trailing-Edge Wing Using Geometrically Exact Vortex Lattice Method

2019 ◽  
Vol 2019 ◽  
pp. 1-15
Author(s):  
Sen Mao ◽  
Changchuan Xie ◽  
Lan Yang ◽  
Chao Yang
Keyword(s):  
Vortex Lattice ◽  
Deflection Angle ◽  
Aircraft Design ◽  
Analysis Method ◽  
Lattice Method ◽  
Trailing Edge ◽  
Vortex Lattice Method ◽  
Analysis And Design ◽  
Aeroelastic Analysis ◽  
Typical Model

A morphing trailing-edge (TE) wing is an important morphing mode in aircraft design. In order to explore the static aeroelastic characteristics of a morphing TE wing, an efficient and feasible method for static aeroelastic analysis has been developed in this paper. A geometrically exact vortex lattice method (VLM) is applied to calculate the aerodynamic forces. Firstly, a typical model of a morphing TE wing is chosen and built which has an active morphing trailing edge driven by a piezoelectric patch. Then, the paper carries out the static aeroelastic analysis of the morphing TE wing and corresponding simulations were carried out. Finally, the analysis results are compared with those of a traditional wing with a rigid trailing edge using the traditional linearized VLM. The results indicate that the geometrically exact VLM can better describe the aerodynamic nonlinearity of a morphing TE wing in consideration of geometrical deformation in aeroelastic analysis. Moreover, out of consideration of the angle of attack, the deflection angle of the trailing edge, among others, the wing system does not show divergence but bifurcation. Consequently, the aeroelastic analysis method proposed in this paper is more applicable to the analysis and design of a morphing TE wing.

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