Numerical Simulation of NASA Trap-Wing Model as a Colombian Contribution to the High-Lift Prediction Workshop

2012 ◽  
Author(s):  
Omar Lopez ◽  
Nicolas Ochoa-Lleras ◽  
Juan Mahecha ◽  
Sebastian Leguizamon ◽  
Jaime Escobar ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
High Lift ◽  
Wing Model

The Influence of the Flight Aerodynamic for Interactions of Wings and Body of the Honeybee

2014 ◽  
Vol 670-671 ◽  
pp. 700-704
Author(s):  
Hong Yan Zhao ◽  
Peng Fei Zhang ◽  
Yun Ma
Keyword(s):  
Numerical Simulation ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Flapping Wing ◽  
High Lift ◽  
Leading Edge Vortex ◽  
Wing Model ◽  
Circulation Mechanism ◽  
Rotation Phase ◽  
Edge Vortex

The flight mechanism of flapping-wing was studied by using the translation-rotation model. We established the flapping-coordinate of the wing, gave the equation of the motion, and simplified the flapping-wing model. The aerodynamic and vortices were simulated by the CFD software of Fluent. The leading-edge vortex generated in the translation phase, and delayed stall mechanism had an important effect on the high lift. In the rotation phase, lift peaks appear due to the wing rapidly rotating and rotational circulation mechanism. The aerodynamics were obtained in different amplitudes, frequencies, angles of attack, the locations of rotating axis and timings of rotation. The influence of these parameters on average lift coefficient is obvious, while it can be ignored to average drag coefficient. Keywords: wing, aerodynamics, vortices, numerical simulation.

scholarly journals Numerical simulation of flow around high lift model in transonic wind tunnels with perspective boundaries

2018 ◽  
Author(s):  
A. I. Ivanov ◽  
I. A. Kursakov ◽  
E. V. Streltsov ◽  
A. O. Volkova
Keyword(s):  
Numerical Simulation ◽  
Wind Tunnels ◽  
High Lift

Characterisation of a highly staggered spanwise cambered biplane

2015 ◽  
Vol 119 (1212) ◽  
pp. 203-228
Author(s):  
L.W. Traub ◽  
R. Waghela ◽  
K.A. Bordignon
Keyword(s):  
Numerical Simulation ◽  
Wind Tunnel ◽  
Dihedral Angles ◽  
Wind Tunnel Testing ◽  
High Lift ◽  
Front Wing ◽  
Geometric Variation ◽  
Tunnel Testing

AbstractAn investigation is presented to elucidate the performance of a staggered, spanwise cambered biplane. The spanwise camber yielded wings forming a ‘∧’ or ‘∨’ when viewed streamwise. The configuration is examined in terms of its aerodynamic and stability characteristics. The feasibility of negating the requirement for a conventional empennage is explored. Geometric variation encompassed front and back wing anhedral/dihedral angles yielding 49 combinations. Evaluation of the geometry was accomplished using both wind tunnel testing and numerical simulation. The results indicated that front wing dihedral in conjunction with aft wing anhedral was most beneficial, such that the benefit of wake spacing was maximised. Aerodynamic benefit was indicated compared to a conventional empennage geometry. The greatest disparity in behaviour of the fore and aft wing anhedral/dihedral distribution was in the high lift regime, where the nature of the stall varied. Simulations to establish the viability of the geometry in terms of controllability were also conducted and indicated that the configuration is viable.

Experimental and Numerical Analysis of the Aerodynamic and Aeroacoustic Properties of a 2D High-Lift Wing Model

2018 ◽  
Author(s):  
Lourenço T. Lima Pereira ◽  
Laura Botero ◽  
Matheus T. de Araujo ◽  
Fernando Catalano ◽  
Danillo C. Reis ◽  
...  
Keyword(s):  
Numerical Analysis ◽  
High Lift ◽  
Wing Model

scholarly journals Investigation of High Lift Force Generation of Dragonfly Wing by a Novel Advanced Mode in Hover

Fluids ◽  
2020 ◽  
Vol 5 (2) ◽  
pp. 59
Author(s):  
Xiaohui Su ◽  
Kaixuan Zhang ◽  
Juan Zheng ◽  
Yong Zhao ◽  
Ruiqi Han ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Energy Expenditure ◽  
Lift Force ◽  
Lift Coefficient ◽  
Aerodynamic Performance ◽  
Dynamic Stall ◽  
Force Generation ◽  
High Lift ◽  
Dragonfly Wing ◽  
Symmetrical Mode

In the paper, a novel flapping mode is presented that can generate high lift force by a dragonfly wing in hover. The new mode, named partial advanced mode (PAM), starts pitching earlier than symmetric rotation during the downstroke cycle of the hovering motion. As a result, high lift force can be generated due to rapid pitching coupling with high flapping velocity in the stroke plane. Aerodynamic performance of the new mode is investigated thoroughly using numerical simulation. The results obtained show that the period-averaged lift coefficient, CL, increases up to 16% compared with that of the traditional symmetrical mode when an earlier pitching time is set to 8% of the flapping period. The reason for the high lift force generation mechanism is explained in detail using not only force investigation, but also by analyzing vortices produced around the wing. The proposed PAM is believed to lengthen the dynamic stall mechanism and enhance the LEV generated during the downstroke. The improvement of lift force could be considered as a result of a combination of the dynamic stall mechanism and rapid pitch mechanism. Finally, the energy expenditure of the new mode is also analyzed.

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