1315 Improvement of Low-Speed Aerodynamic Characteristics for a 60-deg Delta Wing with a Sawtooth Leading Edge

2010 ◽  
Vol 2010.48 (0) ◽  
pp. 417-418
Author(s):  
Yuuki NISHIMURA ◽  
Hiromitsu KAWAZOE ◽  
Takashi MATSUNO
Keyword(s):  
Delta Wing ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Low Speed

20506 The Aerodynamic Characteristics of a Delta Wing with Leading Edge Flaps

2014 ◽  
Vol 2014.20 (0) ◽  
pp. _20506-1_-_20506-2_
Author(s):  
Tadateru ISHIDE ◽  
Hiroki NAKAYAMA ◽  
Kazuya NAGANUMA ◽  
Keiju MAKIMOTO ◽  
Hiroyuki ISHIKAWA ◽  
...  
Keyword(s):  
Delta Wing ◽  
Leading Edge ◽  
Aerodynamic Characteristics

Low-Speed Aerodynamic Characteristics of a Delta Wing with Articulated Wing Tips

2021 ◽  
Author(s):  
Colin W. Trussa ◽  
Clifford A. Whitfield ◽  
Jacob A. Brandon ◽  
Matthew McCrink
Keyword(s):  
Delta Wing ◽  
Aerodynamic Characteristics ◽  
Low Speed ◽  
Wing Tips

Impact of Gurney Flaplike Strips on the Aerodynamic and Vortex Flow Characteristic of a Reverse Delta Wing

2016 ◽  
Vol 138 (6) ◽  
Author(s):  
T. Lee
Keyword(s):  
Vortex Flow ◽  
Delta Wing ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Force Balance ◽  
Vortex Control ◽  
Lift Curve ◽  
Lift And Drag ◽  
The Impact

The impact of Gurney flaplike strips, of different geometric configurations and heights, on the aerodynamic characteristics and the tip vortices generated by a reverse delta wing (RDW) was investigated via force-balance measurement and particle image velocimetry (PIV). The addition of side-edge strips (SESs) caused a leftward shift of the lift curve, resembling a conventional trailing-edge flap. The large lift increment overwhelmed the corresponding drag increase, thereby leading to an improved lift-to-drag ratio compared to the baseline wing. The lift and drag coefficients were also found to increase with the strip height. The SES-equipped wing also produced a strengthened vortex compared to its baseline wing counterpart. The leading-edge strips (LESs) were, however, found to persistently produce a greatly diffused vortex flow as well as a small-than-baseline-wing lift in the prestall α regime. The downward LES delivered a delayed stall and an increased maximum lift coefficient compared to the baseline wing. The LESs provide a potential wingtip vortex control alternative, while the SESs can enhance the aerodynamic performance of the RDW.

Aerodynamic Characteristics and Noise Analysis of a Low-Speed Axial Fan

2018 ◽  
Author(s):  
Bo Luo ◽  
Wuli Chu ◽  
Wei Dong ◽  
Xiangyi Chen
Keyword(s):  
Noise Analysis ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Low Noise ◽  
Axial Fan ◽  
Tonal Noise ◽  
Low Speed ◽  
Optimum Choice ◽  
Aerodynamic Performances ◽  
Axial Fans

Axial fans are widely used in modern industry and new regulations and stringent environmental concerns are prompting manufacturer to design efficient low-noise axial fans. This paper is focused on improving the aerodynamic performances and reducing the tonal noise at BPF and its harmonics by the optimum choice of lean-swept blade and the stacking line for the low-speed axial fan. The aerodynamic characteristics of the axial fan with a shroud are explored by CFD with ANASYS CFX. A hybrid method, SST turbulence model for flow and FW-H equation for acoustics, is chosen to predict the radiated noise. The accuracy and reliability of predicted aerodynamic and aeroacoustics results are verified by comparing both computation and experimental data. A number of modified blades with different leaned angle, swept angle and the stacking lines are modeled and analyzed, and the investigation into the optimum choice of lean-swept blade and the stacking line is conducted according to aerodynamic performances and tonal noise. Q-criterion which can visualize the major flow disturbances is applied for the purpose of identification of acoustic sources. The turbulent flow structures on the leading edge, tip and suction side of the blade are main noise sources. An optimal modification is determined through the analysis of the aerodynamic performances and noise, which is to achieve the desired performances by blade sweep and lean and adjusting the stacking line. The results show that aerodynamic and acoustic performances of the optimized fan are better than that of the original fan and the improvement is more obvious to change the stacking line with centre of gravity compare to blade sweep and lean for the low-speed axial fan.

Aerodynamical Improvement of Delta Wing and Flapping Wing

2015 ◽  
Author(s):  
Tadateru Ishide ◽  
Kazuya Naganuma ◽  
Shinsuke Seiji ◽  
Hiroyuki Ishikawa ◽  
Ryo Fujii ◽  
...  
Keyword(s):  
Force Measurement ◽  
Delta Wing ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Flapping Wing ◽  
Fluid Force ◽  
Unmanned Air Vehicle ◽  
Wide Range ◽  
Air Vehicle ◽  
Piv Analysis

Recently, various studies of Micro Air Vehicle (MAV) and Unmanned Air Vehicle (UAV) have been reported from wide range points of view. The aim of this study are researching the aerodynamic improvement of delta wing and flapping wing in low Reynold’s number region to develop an applicative these air vehicle. Various configurations of Leading Edge Flap (LEF) are used to enhance the aerodynamic characteristics in the delta wing. The six kind of elliptical wings made of stainless steel are used in the flapping wing. The effects of flapping amplitude and wing configuration regarding the aerodynamic characteristics are investigated in detail. The fluid force measurement by six component load cell and PIV analysis are performed as the experimental method. In the flapping wing experiment, the simultaneous measuring of the fluid force measurement and PIV analysis is tried by using the trigger signal from the encoder attached to the flapping model. The relations between the aerodynamic superiority and the vortex behavior around the models are demonstrated.

scholarly journals Pulsed Blowing Interacting with a Leading-Edge Vortex

Aerospace ◽  
2020 ◽  
Vol 7 (1) ◽  
pp. 4
Author(s):  
Andrei Buzica ◽  
Christian Breitsamter
Keyword(s):  
Flow Field ◽  
Delta Wing ◽  
Active Flow Control ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Mean Flow ◽  
Sweep Angle ◽  
Leading Edge Vortex ◽  
Wing Model ◽  
Edge Vortex

Manipulation of vortex instabilities for aerodynamic performance increase is of great interest in numerous aeronautical applications. With increasing angle of attack, the leading-edge vortex of a semi-slender delta wing becomes unsteady and eventually collapses, endangering the flight stability. Hence, active flow control by pulsed blowing stabilizes the vortex system, enlarging the flight envelope for such wing configurations. The most beneficial outcome is the reattachment of the separated shear layer during post-stall, contributing to a lift increase of more than 50%. In contrast to high power consuming brute-force actuation, manipulating the flow instabilities offers a more efficient alternative for mean flow field control, which has direct repercussions on the aerodynamic characteristics. However, the flow mechanisms involving jet–vortex and vortex–vortex interactions and the disturbance convection through the flow field are little understood. This paper reports on the unsteady flow field above a generic half delta wing model with a 65 ° sweep angle and its response to periodic blowing. Numerical and experimental results are presented and discussed in a synergistic manner.

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