Wingtip vortex control via the use of a reverse half-delta wing

Lee, T.; Su, Yunxing

doi:10.1007/s00348-012-1274-8

Cited by 21 publications

(8 citation statements)

References 27 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Validation of static and forced motion flow physics of a canard configured TransCruiser has been simulated (Ghoreyshi, Korkis-kanaan, Jirásek, Cummings, & Lofthouse, 2016). Wingtip vortex control has been learned (T. Lee & Su, 2012). Vortical flow control over delta wing for different sweep back angles has been deeply explored (Kwak, Nelson, Dame, & Dame, 2010).…”

Section: From Stall-delay To Rolled-up Vortex and Vortex Corementioning

confidence: 99%

The Rolled-up and Tip Vortices Studies in the CFD Model of the 3-D Swept-Backward Wind Turbine Blades

Sutrisno

Deendarlianto

Rochmat

et al. 2017

MAS

View full text Add to dashboard Cite

In this paper, the method to analyze of vortex dynamics simulation of 3-D (three dimensional) backward wind turbine blades is introduced, consisted of flow visualization part and detailed measurement part. With this method, one could explain visually and by calculation the role of 3-D flow vortex mechanism patterns on 3-D backward wind turbine blade, the interchange between kinetic and potential energies, the utilization of very strong vortex, which could lose energy, generate lift, and produce tangential mechanical power. The method could be elucidated by analyzing the appearance of rolled-up vortex effect on the 3-D backward wind turbine blades. A sharp pointed backward blade, generally has a weak tip vortex, may generate a second weak vortex center, and appears due to the rolled-up vortex effect, which is quite difficult to identify. The weakness of tip vortex makes the sharp pointed blade more efficient to exchange energy. Blunt backward turbine blades generally have a strong vortex center, a tip vortex; which in the form of a vortex core. Due to the rolled-up vortex effect, it could generate a second weak vortex center that is clearly visible.

show abstract

Section: From Stall-delay To Rolled-up Vortex and Vortex Corementioning

confidence: 99%

The Rolled-up and Tip Vortices Studies in the CFD Model of the 3-D Swept-Backward Wind Turbine Blades

Sutrisno

Deendarlianto

Rochmat

et al. 2017

MAS

View full text Add to dashboard Cite

show abstract

“…Ghoreyshi et al (Ghoreyshi, Cummings, Ronch, & Badcock, 2013) has learned the transonic aerodynamic load modeling of X-31 aircraft, and Ghoreyshi et al (Ghoreyshi, Korkis-kanaan, Jirásek, Cummings, & Lofthouse, 2016) has simulated validation of static and forced motion flow physics of a canard configured TransCruiser, Lee (2012) (Lee & Su, 2012) had learned wingtip vortex control. Kwak et al (Kwak, Nelson, Dame, & Dame, 2010) had studied vortical flow control over delta wings with different sweep back angles.…”

Section: Introductionmentioning

confidence: 99%

The Flow Visualization CFD Studies of the Fuselage and Rolled-up Vortex Effects of the Chengdu J-10-like Fighter Canard

Sutrisno¹,

Rochmat²,

Wibowo³

et al. 2018

MAS

View full text Add to dashboard Cite

Fighter aircrafts with high maneuverability and swiftness are due to fuselage effects, caused by canard-fuselage-main wing configuration. Even though the flows around fighters are highly complex, mostly they create rolled-up vortices capable to delay stalls and increase maximum lifts (Calderon, Wang & Gursul, 2012;Mitchell & Delery, 2001;Boelens, 2012;Chen, Liu, Guo & Qu, 2015). The vortex dynamics analysis method employment is introduced, in this case we focus only on the fighter canard. It characterizes the vortex core, develops the pitching moment & main wing total lift, and exploits the vortex centre visualization, the strength, negative surface pressure and its trajectory. This paper explains the influence of the fighter fuselage, it generates rolled-up vortex effects, causes the flow deflected by the fighter fuselage head, strengthen the vortex centre to become vortex core. Above the aircraft head, due to the curved contour head effect, the second vortex centers are developed makes the vortex center above the head more dynamic.Comparing with fighter without fuselage, the flow property changes, for Chengdu J-10-like model with fuselage, are concentrated at the canard leading edge, where the negative pressures are stronger, since the maximum axial velocities of the vortex centre are higher, and give more distinctive vortex breakdown locations.

show abstract

“…Wen Jing et al have conducted an experimental investigation of static directional stability (Jing, Yankui, & Xueying, 2016), Lee and Su have performed wing-edge eddy supervision through the implementation of a reverse half-DW (Lee & Su, 2012), Mahdi has completed estimation of wing downwash applying simulation (Mahdi, 2015), Lopes and Girardi have reported an investigation of the aerodynamic properties of a wingcanard arrangement with canard distorsion (Lopes & Roberto da Mota Girardi, 2005), and Cai et al have designed of wing-body arrangement optimization to suspend the start of asymmetrical vortex (Cai, Tsai, Luo, & Liu, 2011). Setyawan et al have investigated the application of water tunnel for eddy burst demonstrationon the DW , and completed thorough studies on turbulence models for vortex breakdown detection over DW .…”

Section: Introductionmentioning

confidence: 99%

Performance Analysis and Visualization of Canard and Fuselage Effects on Flow Patterns around a Straight-Body-Type-Fuselage (SBTF) Fighter Models with Experimental Method in Water Tunnel

Sutrisno¹,

Rs²,

Zainuri³

et al. 2018

MAS

View full text Add to dashboard Cite

Performance analysis and visualization of canard and fuselage effects on flow patterns around an SBTF fighter model have been conducted. An SBTF fighter model with an experimental method in a water tunnel would easily reveal visually the vortex dynamics phenomenon that occurred. Testing has been done, with some form of non-canard and canard aircraft in a water tunnel, on vortex dynamics and aerodynamic power on the aircraft model. The stream demonstration used a fluid speed of 0.1 m/s and Reynolds number 6.577x103 on a 1:110 scale model and measured using dye injection method with a print ink type with a mixture ratio of 1:8. The result of the research using GAMA water tunnel showed the aerodynamic force and vortex dynamics phenomenon that happened on the model aircraft. The research on the benefits of the canard is also done by examining the performance and the flow visualization of an SBTF fighter without fuselage, with the symmetrical plane and with the regular fuselage in a water tunnel. The results showed that the use of canard affected the lift, drag, and flow pattern around the wings. The use of canard can enhance the lift of the plane and function to delay the stall by restoring the flow above the wing which should have experienced turbulence back into laminar so that the fighter can maneuver to a higher angle of attack (AoA) without stalling. It is identified that canard and fuselage play significant roles on the design of a fighter. The design choice of the fuselage and the employment of canard are fundamental to support the ability of maneuver and agility of the fighter.

show abstract

Wingtip vortex control via the use of a reverse half-delta wing

Cited by 21 publications

References 27 publications

The Rolled-up and Tip Vortices Studies in the CFD Model of the 3-D Swept-Backward Wind Turbine Blades

The Rolled-up and Tip Vortices Studies in the CFD Model of the 3-D Swept-Backward Wind Turbine Blades

The Flow Visualization CFD Studies of the Fuselage and Rolled-up Vortex Effects of the Chengdu J-10-like Fighter Canard

Performance Analysis and Visualization of Canard and Fuselage Effects on Flow Patterns around a Straight-Body-Type-Fuselage (SBTF) Fighter Models with Experimental Method in Water Tunnel

Contact Info

Product

Resources

About