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Winglet is a lift augmenting device which is attached at the wing tip of an aircraft. Winglets are used to improve the aerodynamic efficiency of an aircraft by lowering the formation of an Induced Drag which is caused by the wingtip vortices. Numerical studies have been carried out to investigate the best aerodynamic performance of a subsonic aircr...
Citations
... In case of takeoff and landing the angle of attack could be set at an angle of 45° so that less vortices are formed, this angle will the induced drag while takeoff and landing, which will reduce takeoff distance. [3], [4], [5] ...
The main purpose of a folding wing tip is to allow aerodynamically efficient high aspect ratio wing. To allow a wing tip to move in flight is to alleviate the loads and achieve lower wing weight or enable wing span to maximize. Thus reduces the induced drag and improve fuel efficiency. The folding wing tip may include spring devices in order to provide an additional gust loads alleviation ability in flight. A wing without a winglet produces wingtip vortices which increases drag as the air from the bottom surface of the wing (high pressure) tries to move to the upper surface (low pressure). To avoid this and have less vortices a winglet is used, around which the flow is same on both surfaces. A folding wingtip can be set at an angle of 0° to have maximum cruise performance and aspect ratio. If the wingtip is set in the range of 15°-50° it can increase lift during take-off. This folding wingtip can access any airport in the world because if it is folded at an angle of 90°, it can meet the gate requirements and restrictions of any airport. To study the performance of this mechanism, the wing tip was designed by using CATIA V5 software. The analysis of the wingtip at different angle of attacks was done using ANSYS and XFLR 5 softwares.
... The main purpose of any winglet is to increase the aircraft aerodynamic effectiveness by decreasing the lift induced drag development at the wing tips [1][2][3][4][5][6][7][8][9][10][11][13][14][15]. The term winglet was previously used to describe an additional lifting surface on an aircraft. ...
Winglets are one of important part of the wing that can reduce the vortex formed at the wing tips and therefore reduce induced drag by partial recovery of the tip vortex energy. Moreover, they increase the effective aspect ratio without actually increasing the wingspan. The geometry of the winglets plays an important role in their task. In the present research, computation of lift and drag of ONERA M6 wing have been conducted using ANSYS Fluent. The results have been validated with the NASA results. Flow features of the entire wing including winglet were examined at different cant angles of winglets of 30°, 60ånd 75° at different angles of attack from 3° to 6°. It is observed that among the cases of this study, wings with winglets produces higher CL/CD ratio than the normal aircraft wing without winglets up to certain degree of angle of attack and by further increasing to higher angle of attack its performance getting diminished. The investigated concept of adaptable angle winglets appears to be a likely substitute for refining the aerodynamic effectiveness of an aircraft.
... .4 Lift/Drag compared with plain wing JEMMME, Vol. ...
Winglet attached on the tip of aircraft wings to increase lift. Mainly, winglet used for increasing aerodynamic efficiency, it decreases induced drag caused by vortex on wings tip. The phenomenon of vortex is collision of high-pressured air below the wings meet the low-pressured air above it that cause turbulence. Induced drag may reach 40% of total drag during cruising, and 80-90% while take off. A procedure to decrease induced drag is using wing tip devices. It used on commercial aircrafts and the most frequently used is blended winglet. Numerical study conducted to examine the best aerodynamic performance of sub-sonic plane wings in angles of attack. Analysis on NACA 23018 airfoil wings with blended winglet on the tip was conducted. Freestream velocity of 40 m/s or Re = 1 × 106, and angle of attack (α) 0o, 5o, 10o, and 15o are used. Evaluation for parameter includes coefficient pressure (Cp), velocity profile, lift, drag, and ratio CL/CD. Obtained contour are pressure contour, velocity, and vorticity. In view of all this, there is increasing performance of aerodynamic with CL/CD ratio of wings with blended winglet and plain wing. Reaching current angle of attack, the function of winglet is gradually decrease.
... Winglet specifically designed as an extension of the wingtip that change the velocity field and pressure as well as reduce the tendency of induced drag thus improving aerodynamic efficiency. [2] FIGURE 2. Tip vortex on fixed wing aircraft (4) One point of the early development of aircraft technology that is important to note is the development by Whitcomb [3] from NASA that uses winglet for the first time on an airplane. Whitchomb giving the foundations of making winglet before being applied to the wing as it is today. ...
... Value of vortices behind different winglet also indicating the effects of induced drag. [2] (a) ...
Winglet is one accessory on airplane wings that can be used to improve wing performance without widen
wingspan wings (wingspan of the aircraft). Winglet serves to dampen the vortex flow at the wing tips that caused by the interaction airflow from upper and lower sides of the wing. [1]. This research was conducted numerical by using simulation model of turbulence k-ε realizable. Freestream velocity is 40 m/s (Re = 5 x 106) with wing angle of attacks (α) = 0o, 2 o, 4 o, 6 o, 8 o, 10 o,12 o, 15 o and 19 o. The Model is NACA airfoil 43018 with and without winglets. Two types wing are used: wingtip fence with forward and rearward. The results show the addition of winglets minimize vorticity magnitude behind the wing. Besides the addition of winglets can improve the aerodynamic performance of the wing with an increase in CL / CD a maximum of 22.9% on a wingtip fence forward and rearward 17.05% on a wingtip fence on theangle of attack 2o. The pressure distribution on lower surface of the wing increase and distributed more evenly compared to that on the plain wing.
... Winglet specifically designed as an extension of the wingtip that change the velocity field and pressure as well as reduce the tendency of induced drag thus improving aerodynamic efficiency. [2] FIGURE 2. Tip vortex on fixed wing aircraft (4) One point of the early development of aircraft technology that is important to note is the development by Whitcomb [3] from NASA that uses winglet for the first time on an airplane. Whitchomb giving the foundations of making winglet before being applied to the wing as it is today. ...
... Value of vortices behind different winglet also indicating the effects of induced drag. [2] (a) ...
Winglet is one accessory on airplane wings that can be used to improve wing performance without widen
wingspan wings (wingspan of the aircraft). Winglet serves to dampen the vortex flow at the wing tips that caused by the interaction airflow from upper and lower sides of the wing.. This research was conducted numerical by using simulation model of turbulence k-ε realizable. Freestream velocity is 40 m/s (Re = 5 x 106) with wing angle of attacks (α) = 0 , 2, 4, 6, 8, 10,12, 15 and 19 degree. The Model is NACA airfoil 43018 with and without winglets. Two types wing are used: wingtip fence with forward and rearward. The results show the addition of winglets minimize vorticity magnitude behind the wing. Besides the addition of winglets can improve the aerodynamic performance of the wing with an increase in CL / CD a maximum of 22.9% on a wingtip fence forward and rearward 17.05% on a wingtip fence on the angle of attack 2 degree. The pressure distribution on lower surface of the wing increase and distributed more evenly compared to that on the plain wing
Pada kelas Airframe, Piston Engine, Gas Turbine Engine. Pada materi pembelajaran ditemukan beberapa permasalahan dalam pemahaman materi tentang performa aerodinamika penerbangan, yaitu Koefisien Lift dan Koefisien Drag pada sayap menggunakan winglet. Winglet dapat memberikan peningkatan performa dengan moderate cost tanpa violating discated spam limit dengan pengembangan metode untuk desain dan analisi winglet telah menjadi focus dari upaya penelitian yang telah berlangsung beberapa tahun terakhir. Mengenai metode penelitian yang akan digunakan yaitu metode simulasi cofisien lift dan coefisien drag dengan software ANSYS FLUENT. Winglet meningkatkan efisiensi bahan bakar dan meningkatkan koefisien lift dan mengurangi koefisien drag dengan menganalisa pengaruh adanya winglet dan non winglet pada pesawat. Benda uji yang akan digunakan adala Airfoil NACA 1410 dan winglet yang di bending dengan (35,45,90) derajat. Rekayasa ukuran winglet diuji menggunkan aplikasi dengan menggunakan perbandingan skala dengan bentuk aslinya. Pembuatan penelitian ini dilakukan agar dapat mengetahui coefisien lift dan drag yang terjadi terhadap penggunaan winglet.
Winglets are equipment that must be used by aircraft and unmanned aerial vehicles (UAV) in the modern era. The function of the winglet is to block the fluid flow jump from the lower side to the upper side on an aircraft wing. With the reduction of fluid flow jumps, it is expected that the wing’s aerodynamic performance will increase. The researchers mostly made geometric variations of the winglets to obtain maximum results, namely the increase of lift and decreasing drag. This research was conducted using Ansys Fluent 19.0 with a turbulent model k-ω SST. The freestream flow rate to be used is 10 m/s (Re = 2.34 × 104) with the angle of attack (α) = 0°, 2°, 4°, 6°, 8°, 10°,12°, 15°, 16°, 17°, 19° and 20°. The model of the specimen is an Eppler 562 airfoil with forward and rearward wingtip fence. From this study, it was found that a winglet with fence height equals the chord line length resulting in better aerodynamic performance than winglet with fence height equal to half the chord line length. It this shows that the winglet with fence height equals the chord line length which can reduce the fluid flow jump from the lower side to the upper side. It was also found that the use of the wingtip fence reduced the strength of vorticity magnitude on the z-axis compared to plain wings. This is due to the vorticity effect of the plain wing and wingtip fence on the flow of fluid passing through it.
Wings are a very important part of aircraft. In that section, most of the lift forces are generated on the airplanes. The aerodynamic performance produced by the wing greatly determines how optimal the cruising range of an aircraft. To improve the performance of the wings, researchers have been competing to make wing modifications of an aircraft. One modification that is used at this time is by adding end wall which is often referred to as a winglet. Winglets function as a barrier to fluid flow jumps from the lower surface to the upper surface. This fluid flow jumps is often called as a tip vortex. One type of winglet discussed in this study is the wingtip fence. This study took wing objects on unmanned aerial vehicle with numerical simulation using Ansys 19.0 software with turbulent model k-ω SST. The freestream flow rate to be used are 10 m/s (Re = 2,34 x 104) and 45 m/s (Re = 1 x 105). The angle of attack used are (α) = 0o, 2o, 4o, 6o, 8o, 10o,12o,15o, 17o, and 19o. The wing model is an Eppler 562 (E562) airfoil with and without a winglet. From this study, it was found that wing aerodynamic performance with Eppler 562 (E562) airfoil was higher at Re = 2,34 x 104. Delay of the stall is more effective at Re = 1 x 105 compared to the Re = 2,34 x 104. But, the aerodynamic performance Re = 2,34 x 104 better than Re = 1 x 105 .
Airfoil modeling is very important especially in determining the airfoil’s performance. One very important in the airfoil design is how to make airfoil with high lift and low drag to obtain a large lift to drag ratio. In this study, the design was carried out with Eppler 562 wing airfoil by adding an endplate at the end of the wing. Endplate used in the form of forward wingtip fence. The addition of endplate at the tip of the wing aims to reduce the occurrence of tip vortex. The emergence of a tip vortex is due to the flow from the lower surface to the upper surface. These tip vortex can cause induced downwash velocities and reduce effective angle of attack. This research is conducted by numerical simulation using simulation software with turbulent model k-ω SST. Freestream flow rate to be used is 10 m/s with angle of attack (α) = 0°, 2°, 4°, 6°, 8°, 10°,12° 15°, 17° and 19°. On forward wingtip fence cant angel 90° produce higher performance than other wing start at α = 6° while forward wingtip fence cant angel 75°.produce better performance at α = 19°. The tip vortices formed by the winglet produce very different shapes to each other and it appears to be a significant effect of the flow field above the wing surface. These vortices will change shape when the angle of attack of the model is changed. The values of the vortices behind the winglet are also different which indicate the effect of induced drag.
