Use Of Winglets Research Articles

Analisis Penggunaan Winglet Pada Pesawat Udara Cessna 150 Dengan Profil NACA 2412

The Cessna 150 is a light aircraft that is widely used in the world of general aviation. One important aspect in designing an aircraft, including the Cessna 150, is the wing design. When there is a meeting of air flows with different pressures from the top and bottom of the aircraft wing, it can cause a vortex to form at each wing tip. The impact of this vortex is that drag force increases, lift force and fuel efficiency decrease and turbulence can occur. One modification to aircraft wings to reduce the impact of these vortices is the use of winglets. This has been widely applied to the latest commercial aircraft to increase aircraft efficiency. The aim of this research is to analyze the use of winglets on a Cessna 150 aircraft with a NACA 2412 profile. This research uses Xflr5 numerical simulation with a 3D geometric configuration. The winglet shape used is cant angle with bend angles of 0°, 15, 30°, 60°, and 90° which were tested at angles of attack of 0°, 3°, 6°, 9°, 12°, 15°, and 18° with an air speed of 46 m/s. The research results show that the NACA 2412 airfoil with winglets is able to increase wing performance efficiency. This is proven by the visualization of air flow in modifications with winglets which can reduce vortices so that the air flow becomes smoother/laminer. In addition, numerical studies show an increase in the value of the lift coefficient (CL), a decrease in the value of the drag coefficient (CD), , and a better / ratio (CL/CD) with the use of winglets, where the winglet efficiency is best at a cant angle with a bend angle of 30°.

On dissecting the wakes of flapping wings

Flapping is an energy-demanding mode of fast animal locomotion that requires physiology, wing kinematics, and unsteady mechanics to work in unison. The trailing flow or wake is a signature of flapping mechanics, which makes it a popular candidate for visualization and analysis. While there are multiple ways to analyze wakes, we need a general framework to ensure utility of the analysis in bio-inspired flapping flight. In this article, we develop a theoretical framework to analyze the transport phenomena of wakes. To illustrate, we apply the theory to a two-dimensional modeled hovering flight comprising engineered rigid flapping plates, which vary in aspect ratio, wingbeat frequency, and the use of winglet. The results potentially explain certain observations in natural flight.

Comparison between the acoustic signatures of a conventional propeller and a tip-loaded propeller with winglets

The Ffowcs-Williams and Hawkings acoustic analogy is utilized to reconstruct the acoustic signature of two marine propellers with and without winglets at the tip of their blades. The database from a large-eddy simulation study is exploited and conducted on a computational grid consisting of about 5 × 109 points. The results of this study demonstrate that tip-loading of the propeller with winglets successfully improves its performance in terms of thrust and efficiency of propulsion. Meanwhile, despite the use of winglets at the tip of the propeller blades, its acoustic signature is reinforced. This result is mainly found attributable to the loading component of sound, originating from the fluctuations of hydrodynamic pressure on the surface of the propellers, in particular at their outer radii: they are significantly higher in the tip-loaded case. In contrast, the non-linear component of sound is similar between the two cases, as a result of the similarity between wake developments and instability behaviors of the structures shed by the conventional and tip-loaded propellers. However, also in this case, the sound coming from the latter is slightly higher, due to the acoustic signature of its stronger tip vortices.

Numerical study of the effect of winglet on the aerodynamic performance of sinusoidal and simple leading-edge wings

PurposeThis study aims to investigate the effectiveness of two types of winglets, multi-tip and raked, on the performance of sinusoidal and simple leading-edge wings and compares it by a numerical method.Design/methodology/approachThe wing configuration in this study is rectangular and uses NACA0020 section, and all simulations are performed by a numerical method based on finite volume and base pressure algorithm in Reynolds 2 × [10]^5. In the mentioned numerical method, the flow is considered turbulent, and the k-ω-SST model is used. To calculate the stresses on the wing surface, the mesh is extended to below the viscous layer, and a second-order upstream accuracy is used to calculate the convection flux.FindingsThe use of raked and multi-tip winglets for the sinusoidal edge of the wing improved aerodynamic performance by 5.12 and 2.28%, respectively, and the greatest effect of these two winglets was on increasing the lifting force and reducing the inductive drag, respectively. Also, by examining the distribution of induced vortices around the configurations, it was found that the curvature of the sinusoidal wing tip at the angles of attack before stall reduced the strength of the induced vortices and, the use of winglet during and after stall, caused increased aerodynamic performance of the sinusoidal wing.Practical implicationsThe whale is an international species of aquatic animal found in most of the world’s oceans. It has large fin aspect ratios that have a series of bulges at the edge of the attack, which improves the aerodynamic performance near and after stall. Today, one of the fields of research is the use of this idea in the wings of micro air vehicle.Originality/valueWinglet reduces induced drag in simple wings. So far, the effect of winglets on wings with sinusoidal attack edges has not been investigated.

Comparison of the winglet aerodynamic performance in unmanned aerial vehicle at low Reynolds number

The Aerodynamic performance of an object is very dependent on the flow of fluid through it and the geometric shape of the object. The use of Unmanned Aerial Vehicle (UAV) demands high aerodynamic performance because it strongly supports the cruising range and fuel or battery used. By reducing drag and increasing the lift optimally, the resulting lift to drag ratio will get maximum results. This study compares the use of winglets in UAVs at low Reynolds numbers. This is very important because generally UAVs are used at low Reynolds numbers. The freestream used is Re = 2.34 x 104 on several low to high angle of attack. The type of airfoil used is Eppler 562 which is equipped with a winglet. Winglets used are simple winglets, blended winglets, and wingtip fence. The geometry was analyzed using numerical simulations namely computational fluid dynamic (CFD). The turbulent model used in this study is K-ω SST on Ansys 19.1. From this study it was found that the use of a wingtip fence produced the best aerodynamic performance compared to other configurations. In addition, the use of a wingtip fence can delay stall and separation better than simple and blended winglets.

Vortex development analysis effects of the use of winglets on Airfoil E562 in unmanned aerial vehicles

The development of aerospace technology is always interesting to follow because designers and manufacturers of flying objects compete to produce the best performance. This invites various forms of objects and geometries to be studied and researched. The use of winglets is commonly used in flying objects in the world today. This study further explores the effects of using winglets on vortex formation in areas near the wing’s body and behind it. This research uses computational fluid dynamics using Ansys 19.1. The turbulent model used is k-ω SST with a Reynolds number of 2.34 x 104. The observed angle of attacks are 15° and 17° on Eppler 562 wing airfoil. This research found that each winglet configuration has different velocity path lines and vorticity magnitude characteristics different. In the areas where fluid flow jumps occur it is shown that there is an increase in fluid flow velocity. The forward wingtip fence can withstand the fluid flow jump better than other winglet configurations. The use of winglets results in a greater area of vorticity magnitude behind the wing than the plain wing even though the forward and rearward wingtip fence produces smaller values, especially behind the wing.

Numerical Study of Secondary Flow Characteristics on the Use of the Winglets

The upper surface of the wing is constantly observed by experts on the wing. In this area, a variety of phenomena cause how much aerodynamic performance is demonstrated. Changing or adding geometry to the wing changes the flow characteristics of the upper surface. The use of winglets will certainly change the flow characteristics around the wingtip which will have a large effect on the area behind and next to the winglet itself. This research was carried out using Ansys 19.1 and the turbulent k-ω SST model. The airfoil used is Eppler 562 which is commonly used in unmanned aerial vehicles. Freestream flow velocity that will be used is 10 m/s (Re = 2.34 x 104) with an angle of attack (α) = 12° and 15°. From this study, it was found that the pressure contour in the y-z plane showed a reduction in area and intensity through the use of winglets. Secondary flow formed by using the forward wingtip fence results in a smaller area around the wingtip area than other configurations. Besides, the value of pressure on the upper surface which is equipped with a forward wingtip fence shows that pressure is still quite high when compared to the others.

Improving aircraft fuel efficiency by using the adaptive wing and winglets

Improving the aircraft’s fuel efficiency is one of the main requirements for prospective and modernized aircraft. This paper reports the assessment of change in aerodynamic quality resulting in the improved fuel efficiency of a long-range aircraft when using promising means to enhance aerodynamic quality. These means include the abandonment of the mechanization of wing edges and conventional controls through the use of an adaptive wing, the artificial laminarization of the flow around the elements of a glider, the application of winglets. The abandonment of conventional wing controls and wing mechanization is predetermined by the need to ensure a seamless surface of the glider elements to prevent the premature turbulization of the flow that consequently leads to a decrease in the profile drag of an aircraft. The use of winglets is aimed at reducing inductive drag. Determining a change in the aircraft’s fuel efficiency would make it possible to estimate a change in the operating costs during its life cycle.The study employed the known modular software complex «Integration 2.1». The engineering and navigational calculation was performed for a typical flight profile of a long-range aircraft. The possibility of reducing fuel consumption by up to 20 % has been shown. The largest impact on the decrease in fuel consumption is exerted by the flow laminarization on the surface of the glider elements; the reduction in fuel consumption was 17.1 %. The abandonment of mechanization and ailerons decreases fuel consumption by 3.9 %, while the abandonment of ailerons, slats, and flaps reduces fuel consumption by 0.4, 1.5, and 0.4 %, respectively. The use of spiroid winglets made it possible to reduce fuel consumption by 1.95 %

Aerodynamics Analisys of the Wingtip Fence Effect on UAV Wing

Winglets have an important effect in the use of aircraft and of unmanned aerial vehicle (UAV). The expected effect in winglet usage is the increase of the lift coefficient and the decrease of the drag coefficient. These aspects play a very important role in determining aerodynamic performance. Many researches have been done in order to determine the most effective winglet designs to further explore the effects on aircraft and unmanned aerial vehicle (UAV). Based on that fact, in this study the use of winglet on UAV is discussed. This research has been conducted using a simulation software with turbulent model k-ω SST. The freestream velocity used is 10 m / s (Re=2.3 × 104) with an angle of attack (α) = 0o, 2o, 4o, 6o, 8o, 10o,12o, 15o, 16o, 17o and 19o. Model specimens are airfoils Eppler 562 with and without winglet. Winglet used in this study are wingtip fences with forward and rearward configuration. From the research, it has been found that the addition of winglet can minimize vorticity magnitude behind the wing especially forward wingtip fence. Forward wingtip fence results in a smaller vorticity area than plain wing and rearward wingtip fence although the vorticities increase with the increase of the angles of attack. In addition, the forward wingtip fence can prevent the formation of tip vortex better than the rearward one.

Numerical study of flow characteristics on wing airfoil eppler 562 with whitcomb winglet variations

Winglet is a tool used to improve the efficiency of aircraft and UAV performance by preventing fluid flow jump from lower surface to upper surface at wingtip. The addition of this winglet resulted in improved lift and reduction of drag force from the aircraft wing or UAV. From Whitcomb's research, it was found that the use of winglet on a full size airplane can increase fuel efficiency by 7%. The research led to the idea of conducting research on fluid flow characteristics on the UAV wing with the Eppler 562 airfoil combined with the whitcomb winglet. This numerical study was conducted using the Computational Fluid Dynamics (CFD) method based on the advantages of using this simulation that can review the fluid flow in macroscopic way. This study is provide accurate fluid flow visualization results and can improve the performance of the wings when compared with wings without winglet (plain wing). Wing with the Eppler 562 airfoil combined with the whitcomb winglet results reduction in rotating motion that makes velocity components as opposed to lift.

Numerical Study of Heat Transfer Enhancement in Solar Air Heater Duct Fitted with Delta Winglets

The paper brings Numerical study of thermal performance of solar air heater channel in which delta winglet type vortex generators with and without holes punched on it are attached. Delta winglet type vortex generators having holes punched onto it are fitted in an array having 5 pair in one row, having 3 such rows starting at the entry of test section. With pitch of 60mm.Deltawinglet pair have an attack angle of 30 degrees, with height of winglet equal to half of duct height The study is carried out for Reynolds’s No in the range of 5000 to 25000 by changing airflow rate.in the test section with its upper channel wall provided with a uniform heat flux. Results are then compared with that of duct mounted with delta winglet without holes. Thermal performance is evaluated by analyzing both friction factor and Nussult’s number using R L Webb’s correlation for surfaces with roughness. Numerical simulation is done using Ansys fluent software. Analysis findings says that use of winglets brings enhancement in the heat transfer and thus increases the thermal performance. Arrangement of winglets also influences the performance. Improvements in design and performance can be brought by using winglets with different attack angles and span length.

Animal Aloft: The Origins of Aerial Behavior and Flight

Diverse taxa of animals exhibit remarkable aerial capacities, including jumping, mid-air righting, parachuting, gliding, landing, controlled maneuvers, and flapping flight. The origin of flapping wings in hexapods and in 3 separate lineages of vertebrates (pterosaurs, bats, and birds) greatly facilitated subsequent diversification of lineages, but both the paleobiological context and the possible selective pressures for the evolution of wings remain contentious. Larvae of various arboreal hemimetabolous insects, as well as many adult canopy ants, demonstrate the capacity for directed aerial descent in the absence of wings. Aerial control in the ancestrally wingless archaeognathans suggests that flight behavior preceded the origins of wings in hexapods. In evolutionary terms, the use of winglets and partial wings to effect aerial righting and maneuvers could select for enhanced appendicular motions, and ultimately lead to powered flight. Flight behaviors that involve neither flapping nor wings are likely to be much more widespread than is currently recognized. Further characterization of the sensory and biomechanical mechanisms used by these aerially capable taxa can potentially assist in reconstruction of ancestral winged morphologies and facilitate our understanding of the origins of flight.

Effects of winglets to augment tube wall heat transfer in louvered fin heat exchangers

The louvered fin heat exchanger, a type of compact heat exchanger, has been used heavily in the automotive and air conditioning industries for the last several decades. The majority of past research, aimed towards improving louvered fin exchanger efficiency, has focused on optimizing various parameters of the louvered fin. The experimental study presented in this paper concentrates instead on augmenting the heat transfer along the tube wall of the compact heat exchanger through the use of winglets placed on the louvers. The experiments were completed on a 20 times scaled model of an idealized louvered fin exchanger with a fin pitch to louver pitch ratio of 0.76 and a louver angle of 27°. The Reynolds numbers tested, based on louver pitch, were between 230 and 1016. A number of geometrical winglet parameters, including angle of attack, aspect ratio, direction, and shape, were all evaluated based on heat transfer augmentation, friction factor augmentation, and efficiency index (combination of both augmentations). In an attempt to optimize these winglet parameters, tube wall heat transfer augmentations as high as 39% were achieved with associated friction factor augmentations as high as 23%.

Winglets on low-aspect-ratio wings

The drag reduction potentially available from the use of winglets at the tips of low aspect ratio (1.75-2.67) wings with pronounced (45-60 deg) leading edge sweep is assessed numerically for the case of a cruise design point at Mach of 0.8 and a lift coefficient of 0.3. Both wing-winglet and wing-alone design geometries are derived from a linear-theory, minimum induced drag design methodology. Relative performance is evaluated with a nonlinear extended small disturbance potential flow analysis code. Predicted lift coefficient/pressure drag coefficient increases at equal lift for the wing-winglet configurations over the wing-alone planform are of the order of 14.6-15.8, when boundary layer interaction is included.