Calculation of Blade-Vortex Interaction of Rotary Wings in Incompressible Flow by an Unsteady Vortex-Lattice Method Including Free Wake Analysis

1992 ◽  
pp. 153-166 ◽  
Author(s):  
A. Röttgermann ◽  
R. Behr ◽  
Ch. Schöttl ◽  
S. Wagner
Keyword(s):  
Incompressible Flow ◽  
Vortex Lattice ◽  
Vortex Interaction ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Blade Vortex Interaction ◽  
Rotary Wings ◽  
Free Wake

A Hybrid Free Wake Simulation Comparison of Turbine Wake Steering With Innovative Turbine Designs

2017 ◽  
Author(s):  
Keye Su ◽  
Donald B. Bliss
Keyword(s):  
Wind Farm ◽  
Vortex Lattice ◽  
Wind Farms ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Turbine Efficiency ◽  
Unsteady Effects ◽  
Free Wake ◽  
Turbine Wake ◽  
Far Wake

Wake shielding in wind farms caused by the interaction of upstream energy-depleted wakes and down-stream turbines substantially reduces individual turbine efficiency and overall wind farm performance. A method is studied to alleviate this problem using shaft tilting to steer wakes upward and reduce the interaction with downstream turbines. Simulations have been conducted to verify this method and to assess its effectiveness. These simulations employ a specially developed hybrid free wake method that combines a Constant Circulation Contour Model, suitable for downwind far-wake evolution, with a Vortex Lattice Method, leading to accurate blade air-loads calculation, including unsteady effects, stall, and reduced complexity. The interaction of two inline tipped axis turbines has been analyzed to assess the advantages and challenges of wake steering in a system of turbines. Beyond the traditional HAWT, two unconventional turbine configurations have been studied with the intent to further increase wake ascent.

scholarly journals On the aerodynamic interactions analysis between the main rotor and the helicopter fuselage

10.29007/3m41 ◽  
2020 ◽  
Author(s):  
Thanh Dong Pham ◽  
Anh Tuan Nguyen ◽  
Ngoc Thanh Dang ◽  
Vu Uy Pham
Keyword(s):  
Aerodynamic Characteristic ◽  
Vortex Lattice ◽  
Aerodynamic Characteristics ◽  
Main Rotor ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Wake Model ◽  
Helicopter Main Rotor ◽  
Flight Regimes ◽  
Free Wake

This paper develops a numerical method that is capable of analyzing the aerodynamic characteristic of the helicopter main rotor in consider the influence of fuselage. The method is based on an unsteady nonlinear vortex-lattice method that can be used to simulate the interactions among the helicopter components efficiently. To clarify the effect of the main rotor-fuselage interaction, the aerodynamic characteristics of the main rotor in consider the influence of fuselage is determined along with those of the combined main rotor-fuselage system. The paper also shows the velocity field and free wake model in several flight regimes. The fuselage is modeled as a streamlined object, which is discretized into the system of quadrilateral vortex panels. The no-penetration boundary condition is satisfied on the fuselage surface, and no vorticity is shed from the fuselage. The results obtained in this paper are validated against experimental data and some from previous numerical methods.

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.

scholarly journals Static aeroelastic analysis of very flexible wings based on non-planar vortex lattice method

2013 ◽  
Vol 26 (3) ◽  
pp. 514-521 ◽  
Author(s):  
Changchuan Xie ◽  
Libo Wang ◽  
Chao Yang ◽  
Yi Liu
Keyword(s):  
Vortex Lattice ◽  
Lattice Method ◽  
Flexible Wings ◽  
Vortex Lattice Method ◽  
Aeroelastic Analysis

scholarly journals Analysis of wing flap configurations by a nonplanar vortex lattice method

1988 ◽  
Vol 25 (2) ◽  
pp. 97-98 ◽  
Author(s):  
B. Rajeswari ◽  
H. N. V. Dutt
Keyword(s):  
Vortex Lattice ◽  
Lattice Method ◽  
Vortex Lattice Method
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