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.

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.

Some Comments on High-Lift Testing in Wind Tunnels with Particular Reference to Jet-Blowing Models

1957 ◽  
Vol 61 (560) ◽  
pp. 529-540 ◽  
Author(s):  
A. Anscombe ◽  
J. Williams
Keyword(s):  
Wind Tunnel ◽  
Compressed Air ◽  
Model Construction ◽  
Wind Tunnels ◽  
Wind Tunnel Testing ◽  
Test Technique ◽  
High Lift ◽  
General Test ◽  
Jet Blowing ◽  
Current Experience

SummaryThis paper considers some of the special problems of wind tunnel testing which arise in high-lift work. Discussion is confined to current experience in the R.A.E. and N.P.L. low-speed wind tunnels, and refers mainly to tests on blowing over flaps or jet-flaps. Comments are made on suitable size of model, methods of feeding compressed air into models without affecting balance readings, and general test technique. Methods of model construction are not specifically discussed.

Numerical Simulation of Half-Span Aircraft Model with High-Lift Devices in Wind Tunnel

2008 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Yuzuru Yokokawa ◽  
Kentaro Tanaka ◽  
Kazuomi Yamamoto ◽  
Takeshi Ito
Keyword(s):  
Numerical Simulation ◽  
Wind Tunnel ◽  
High Lift ◽  
Aircraft Model

Numerical Simulation of Powered High-Lift Flow

2014 ◽  
Vol 1016 ◽  
pp. 501-505
Author(s):  
Zhi Bin Gong ◽  
Jie Li ◽  
Bin Tian
Keyword(s):  
Numerical Simulation ◽  
Point Of View ◽  
Circulation Control ◽  
High Lift ◽  
The Past

To achieve short-take-off-and-landing (STOL) performance, numerous airframe/propulsion integration (API) technologies have been developed for military and commercial transports. Powered lift technology refers to a concept of utilizing the propulsion exhaust flows to increase lift through an increase in wing circulation []. Over the past seventy years, various concepts have been explored to accomplish this goal. From the point of view of technical characteristics, powered lift concepts can be sorted into three groups: a circulation control wing, blown flaps, and jet wing. Most of other concepts are slight deviations of these three.

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