Gurney flap scaling for optimum lift-to-drag ratio

During airplane’s take-off, higher lift force should be provided by wing used high lift devices, and the drag should be lower. The design basis of high lift devices with good aerodynamic characteristic is the design of the multi-element airfoil. When a multi-element airfoil is used Gurney flap, lift coefficient can be improved while drag coefficient is also increased, but the lift-to-drag ratio is reduced. In this paper, the numerical simulation method is used to study the aerodynamic characteristic of the multi-element airfoil used Gurney flap with slat in the configuration of take-off. Lift coefficient and drag coefficient of the multi-element airfoil with Gurney flap can be reduced by slat while lift-to-drag ratio of airfoil is increased. Through the comparisons of the multi-element airfoils with Gurney flap with different types of slats, the optimized multi-element airfoil with higher lift coefficient and lower drag coefficient is obtained ultimately.

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Parametric Study of a Gurney Flap Implementation in a DU91W(2)250 Airfoil

Energies ◽

10.3390/en12020294 ◽

2019 ◽

Vol 12 (2) ◽

pp. 294 ◽

Cited By ~ 14

Author(s):

Iñigo Aramendia ◽

Unai Fernandez-Gamiz ◽

Ekaitz Zulueta ◽

Aitor Saenz-Aguirre ◽

Daniel Teso-Fz-Betoño

Keyword(s):

Prediction Model ◽

Parametric Study ◽

Aerodynamic Performance ◽

Slight Improvement ◽

Aerodynamic Efficiency ◽

Flow Control Devices ◽

Gurney Flap ◽

Control Devices ◽

Drag Ratio ◽

Lift To Drag Ratio

The growth in size and weight of wind turbines over the last years has led to the development of flow control devices, such as Gurney flaps (GFs). In the current work, a parametric study is presented to find the optimal GF length to improve the airfoil aerodynamic performance. Therefore, the influence of GF lengths from 0.25% to 3% of the airfoil chord c on a widely used DU91W(2)250 airfoil has been investigated by means of RANS based numerical simulations at Re = 2 × 106. The numerical results showed that, for positive angles of attack, highest values of the lift-to-drag ratio CL/CD are obtained with GF lengths between 0.25% c and 0.75% c. Particularly, an increase of 21.57 in CL/CD ratio has been obtained with a GF length of 0.5% c at 2° of angle of attack AoA. The influence of GFs decreased at AoAs larger than 5°, where only a GF length of 0.25% c provides a slight improvement in terms of CL/CD ratio enhancement. Additionally, an ANN has been developed to predict the aerodynamic efficiency of the airfoil in terms of CL/CD ratio. This tool allows to obtain an accurate prediction model of the aerodynamic behavior of the airfoil with GFs.

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Lift-to-Drag Ratio Enhancement for a Wing Using Thermal Forcing

AIAA Aviation 2019 Forum ◽

10.2514/6.2019-3599 ◽

2019 ◽

Author(s):

Mehul Varshney ◽

Anchal Varshney ◽

MF Baig

Keyword(s):

Thermal Forcing ◽

Drag Ratio ◽

Lift To Drag Ratio

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A Parametric Study of Trailing Edge Flap Implementation on Three Different Airfoils Through an Artificial Neuronal Network

Symmetry ◽

10.3390/sym12050828 ◽

2020 ◽

Vol 12 (5) ◽

pp. 828

Author(s):

Igor Rodriguez-Eguia ◽

Iñigo Errasti ◽

Unai Fernandez-Gamiz ◽

Jesús María Blanco ◽

Ekaitz Zulueta ◽

...

Keyword(s):

Aerodynamic Coefficients ◽

Trailing Edge ◽

High Lift ◽

Trailing Edge Flaps ◽

Artificial Neural Network Ann ◽

Lift And Drag ◽

Artificial Neuronal Network ◽

Naca 0012 ◽

Drag Ratio ◽

Lift To Drag Ratio

Trailing edge flaps (TEFs) are high-lift devices that generate changes in the lift and drag coefficients of an airfoil. A large number of 2D simulations are performed in this study, in order to measure these changes in aerodynamic coefficients and to analyze them for a given Reynolds number. Three different airfoils, namely NACA 0012, NACA 64(3)-618, and S810, are studied in relation to three combinations of the following parameters: angle of attack, flap angle (deflection), and flaplength. Results are in concordance with the aerodynamic results expected when studying a TEF on an airfoil, showing the effect exerted by the three parameters on both aerodynamic coefficients lift and drag. Depending on whether the airfoil flap is deployed on either the pressure zone or the suction zone, the lift-to-drag ratio, CL/CD, will increase or decrease, respectively. Besides, the use of a larger flap length will increase the higher values and decrease the lower values of the CL/CD ratio. In addition, an artificial neural network (ANN) based prediction model for aerodynamic forces was built through the results obtained from the research.

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Fluid–structure interaction simulation on flight performance of a dragonfly wing under different pterostigma weights

Journal of Mechanics ◽

10.1093/jom/ufaa013 ◽

2021 ◽

Vol 37 ◽

pp. 216-229

Author(s):

Yung Jeh Chu ◽

Poo Balan Ganesan ◽

Mohamad Azlin Ali

Keyword(s):

Optimization Design ◽

Fluid Structure Interaction ◽

Spatial Location ◽

Fluid Structure ◽

Structure Interaction ◽

Dragonfly Wing ◽

Interaction Simulation ◽

Wing Performance ◽

Drag Ratio ◽

Lift To Drag Ratio

Abstract The dragonfly wings provide insights for designing an efficient biomimetic micro air vehicle (BMAV). In this regard, this study focuses on investigating the effect of the pterostigma weight loading and its spatial location on the forewings of dragonfly by using the fluid–structure interaction simulation. This study also investigates the effect of change in the wing elasticity and density on the wing performance. The forewing, which mimics the real dragonfly wing, is flat with a 47.5 mm span and a 0.4 mm thickness. The wing was set to cruise at 3 m/s with a constant flapping motion at a frequency of 25 Hz. This study shows that a small increase of pterostigma loading (11% of wing weight) at the tip of the wing significantly improves the lift to drag ratio, CL/CD, which has 129.16% increment in comparison with no loading. The lift to drag ratio depends on the pterostigma location, pterostigma loading, elastic modulus and density. The results of this study can be used as a reference in future BMAV wing optimization design.

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Aerodynamic study of single corrugated variable-camber morphing aerofoil concept

The Aeronautical Journal ◽

10.1017/aer.2021.71 ◽

2021 ◽

pp. 1-29

Author(s):

K. Dhileep ◽

D. Kumar ◽

P.N. Gautham Vigneswar ◽

P. Soni ◽

S. Ghosh ◽

...

Keyword(s):

Finite Volume ◽

Interpolation Method ◽

Beam Theory ◽

Small Deformation ◽

Aerodynamic Characteristics ◽

Ansys Fluent ◽

Aerodynamic Efficiency ◽

Finite Element Software ◽

Drag Ratio ◽

Lift To Drag Ratio

Abstract Camber morphing is an effective way to control the lift generated by any aerofoil and potentially improve the range (as measured by the lift-to-drag ratio) and endurance (as measured by $C_l^{3/2}/C_d$ ). This can be especially useful for fixed-wing Unmanned Aerial Vehicles (UAVs) undergoing different flying manoeuvres and flight phases. This work investigates the aerodynamic characteristics of the NACA0012 aerofoil morphed using a Single Corrugated Variable-Camber (SCVC) morphing approach. Structural analysis and morphed shapes are obtained based on small-deformation beam theory using chain calculations and validated using finite-element software. The aerofoil is then reconstructed from the camber line using a Radial Basis Function (RBF)-based interpolation method (J.H.S. Fincham and M.I. Friswell, “Aerodynamic optimisation of a camber morphing aerofoil,” Aerosp. Sci. Technol., 2015). The aerodynamic analysis is done by employing two different finite-volume solvers (OpenFOAM and ANSYS-Fluent) and a panel method code (XFoil). Results reveal that the aerodynamic coefficients predicted by the two finite-volume solvers using a fully turbulent flow assumption are similar but differ from those predicted by XFoil. The aerodynamic efficiency and endurance factor of morphed aerofoils indicate that morphing is beneficial at moderate to high lift requirements. Further, the optimal morphing angle increases with an increase in the required lift. Finally, it is observed for a fixed angle-of-attack that an optimum morphing angle exists for which the aerodynamic efficiency becomes maximum.

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Hydrodynamic Evaluation of a Generic Sail Used in an Innovative Prawn-Trawl Otter Board

Volume 6: Ocean Space Utilization ◽

10.1115/omae2015-41335 ◽

2015 ◽

Cited By ~ 2

Author(s):

Cheslav Balash ◽

David Sterling ◽

Matt Broadhurst ◽

Arno Dubois ◽

Morgan Behrel

Keyword(s):

Degrees Of Freedom ◽

Design Feature ◽

Hydrodynamic Characteristics ◽

Flat Plates ◽

Successful Operation ◽

Six Degrees Of Freedom ◽

Recent Innovation ◽

Hydrodynamic Evaluation ◽

Drag Ratio ◽

Lift To Drag Ratio

In prawn-trawling operations, otter boards provide the horizontal force required to maintain net openings, and are typically low aspect ratio (∼0.5) flat plates operating on the seabed at high angles of attack (AOA; 35–40°). Such characteristics cause otter boards to account for up to 30% of the total trawling resistance, including that from the vessel. A recent innovation is the batwing otter board, which is designed to spread trawls with substantially less towing resistance and benthic impacts. A key design feature is the use of a sail, instead of a flat plate, as the hydrodynamic foil. The superior drag and benthic performance of the batwing is achieved by (i) successful operation at an AOA of ∼20° and (ii) having the heavy sea floor contact shoe in line with the direction of tow. This study investigated the hydrodynamic characteristics of a generic sail by varying its twist and camber, to identify optimal settings for maximum spreading efficiency and stability. Loads in six degrees of freedom were measured at AOAs between 0 and 40° in a flume tank at a constant flow velocity, and with five combinations of twist and camber. The results showed that for the studied sail, the design AOA (20°) provides a suitable compromise between greater efficiency (occurring at lower AOAs) and greater effectiveness (occurring at higher AOAs). At optimum settings (20°, medium camber and twist), a lift-to-drag ratio >3 was achieved, which is ∼3 times more than that of contemporary prawn-trawling otter boards. Such a result implies relative drag reductions of 10–20% for trawling systems, depending on the rig configuration.

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Review of space vehicle control and guidance methods at atmosphere reentry

Keldysh Institute Preprints ◽

10.20948/prepr-2021-5 ◽

2021 ◽

pp. 1-20

Author(s):

Alexander Sergeevich Samotokhin

Keyword(s):

Space Vehicle ◽

Vehicle Control ◽

Control Methods ◽

The Moon ◽

Reentry Vehicles ◽

Drag Ratio ◽

Lift To Drag Ratio

Review of control methods for statically stable reentry vehicles with low lift-to-drag ratio at returning from the Moon is presented. We are considering algorithms that have been used in Soviet and American Moon programs, as well as advanced algorithms that now are developed. General trends of advanced domestic and foreign methods are determined.

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Aerodynamic and Vibration Characteristics of the Micro-Octocopter at Low Reynolds Number

Mobile Information Systems ◽

10.1155/2021/3691559 ◽

2021 ◽

Vol 2021 ◽

pp. 1-9

Author(s):

Xiaohua Zou ◽

Mingsheng Ling ◽

Wenzheng Zhai

Keyword(s):

Reynolds Number ◽

Load Capacity ◽

Lift Coefficient ◽

Angle Of Attack ◽

Aerodynamic Characteristics ◽

Vibration Characteristics ◽

Low Reynolds ◽

Vibration Performance ◽

Drag Ratio ◽

Lift To Drag Ratio

With the development of flight technology, the need for stable aerodynamic and vibration performance of the aircraft in the civil and military fields has gradually increased. In this case, the requirements for aerodynamic and vibration characteristics of the aircraft have also been strengthened. The existing four-rotor aircraft carries limited airborne equipment and payload, while the current eight-rotor aircraft adopts a plane layout. The size of the propeller is generally fixed, including the load capacity. The upper and lower tower layout analyzed in this paper can effectively solve the problems of insufficient four-axis load and unstable aerodynamic and vibration performance of the existing eight-axis aircraft. This paper takes the miniature octorotor as the research object and studies the aerodynamic characteristics of the miniature octorotor at different low Reynolds numbers, different air pressures and thicknesses, and the lift coefficient and lift-to-drag ratio, as well as the vibration under different elastic moduli and air pressure characteristics. The research algorithm adopted in this paper is the numerical method of fluid-solid cohesion and the control equation of flow field analysis. The research results show that, with the increase in the Reynolds number within a certain range, the aerodynamic characteristics of the miniature octorotor gradually become better. When the elastic modulus is 2.5 E, the aircraft’s specific performance is that the lift increases, the critical angle of attack increases, the drag decreases, the lift-to-drag ratio increases significantly, and the angle of attack decreases. However, the transition position of the flow around the airfoil surface is getting closer to the leading edge, and its state is more likely to transition from laminar flow to turbulent flow. When the unidirectional carbon fiber-reinforced thickness is 0.2 mm and the thin arc-shaped airfoil with the convex structure has a uniform thickness of 2.5% and a uniform curvature of 4.5%, the aerodynamic and vibration characteristics of the octorotor aircraft are most beneficial to flight.

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