Investigation of a NACA0012 Finite Wing Aerodynamics at Low Reynold’s Numbers and 0º to 90º Angle of Attack

Airfoil Surface ◽

Wing Geometry ◽

Stall Angle ◽

Finite Wing ◽

Lift And Drag

The aerodynamic characteristics of a NACA0012 wing geometry at low Reynold’s numbers and angle of attack ranging from 0º to 90º are investigated using numerical simulations and the results are validated by wind tunnel experiments. Further experiments are conducted at low Reynold’s numbers of 1 × 105, 2 × 105 and 3 × 105. Findings of the study show a similar trend for the lift and drag coefficients at all the investigated Reynold’s numbers. The lift coefficient is linearly increased with angle of attack until it reaches its maximum value at 32º which is the stall angle. It is observed that further increment in angle of attack results in decrement of lift coefficient until it reaches its minimum value at 90º angle of attack. The drag force acting on the airfoil increases as the angle of attack is increased and increment in the drag force results in change of laminar flow to turbulent flow. As the turbulence gets higher the flow starts to separate from the airfoil surface due to eddies generated by turbulence. Hence, the lift force generated by the wing is reduced and drag force is increased simultaneously, which results in poor performance of the wing.

Analysis on Flow Field Characteristics of Airfoil in Pitching Motion

10.1088/1742-6596/2076/1/012069 ◽

2021 ◽

Vol 2076 (1) ◽

pp. 012069

Author(s):

Rui Yin ◽

Jing Huang ◽

Zhi-Yuan He

Keyword(s):

Flow Field ◽

Drag Coefficient ◽

Lift Coefficient ◽

Angle Of Attack ◽

Decisive Role ◽

Pitching Motion ◽

Maximum Value ◽

Flow Field Characteristics ◽

Lift And Drag

Abstract Based on CFD, the flow field characteristics of NACA4412 airfoil are analyzed under pitching motion, and its aerodynamic characteristics are interpreted. The results show that streamline changes on the upper surface of the airfoil play a decisive role in the aerodynamic characteristics. The interaction between the vortex leads to fluctuations in the lift and drag coefficients. Under a big angle of attack, the secondary trailing vortex on the upper surface of the airfoil adheres to the trailing edge of the airfoil, resulting in an increased drag coefficient. Under a small angle of attack, the secondary trailing vortex can break away from the airfoil. The lift coefficient reaches the maximum value of 2.961 before the airfoil is turned upside down, and the drag coefficient reaches the maximum value of 1.515 after the airfoil is turned upside down, but the corresponding angles of attack of the two are equal.

Volume 8: Energy Systems: Analysis, Thermodynamics and Sustainability; Sustainable Products and Processes ◽

Selection of Airfoils for Straight-Bladed Vertical Axis Wind Turbines Based on Desirable Aerodynamic Characteristics

10.1115/imece2008-66027 ◽

2008 ◽

Cited By ~ 2

Author(s):

Mazharul Islam ◽

M. Ruhul Amin ◽

David S.-K. Ting ◽

Amir Fartaj

Keyword(s):

Urban Areas ◽

Lift Coefficient ◽

Vertical Axis ◽

Performance Indices ◽

Niche Markets ◽

Design Changes ◽

Stall Angle ◽

Lift And Drag ◽

Selection Of

Selection of the airfoil is crucial for better aerodynamic performance and dimensions of a smaller-capacity SB-VAWT which can compete with conventional energy sources in niche markets like urban areas and off-grid remote applications for diversified applications. Airfoil related design changes also have the potential for increasing the cost effectiveness of VAWTs. Recently, Islam et. al [1] have identified the desirable features of an ideal airfoil for smaller capacity SB-VAWT to improve its starting characteristics and overall performance. They have shortlisted several aerodynamic characteristics of the desirable airfoil. Based on these desirable aerodynamic characteristics, an attempt has been made in this paper to shortlist ten prospective candidate airfoils for smaller-capacity SB-VAWT. This is done using both experimental and analytical characteristics. Nine performance indices have been defined in this paper in light of desirable aerodynamic characteristics to select best performing airfoil. These performance indices are utilized for considering the following desirable aerodynamic characteristics: (i) stall angle at low Reynolds number, (ii) width of the drag bucket, (iii) zero-lift-drag coefficient, (iv) Cl/Cd ratio, (v) maximum lift-coefficient, (vi) deep-stall angle, (vii) roughness sensitivity, (viii) trailing edge noise generation, and (ix) pitching moment. Here, Cl and Cd are coefficients of lift and drag respectively. After determining the value of the performance indices and rating of the candidate airfoils, the most promising airfoil is selected. Among the ten candidate airfoils, overall rating of NASA LS(1)-0417 has been found to be the best.

Effect of Reynolds Number on Aerodynamics of Airfoil with Gurney Flap

International Journal of Rotating Machinery ◽

10.1155/2015/628632 ◽

2015 ◽

Vol 2015 ◽

pp. 1-10 ◽

Cited By ~ 5

Author(s):

Shubham Jain ◽

Nekkanti Sitaram ◽

Sriram Krishnaswamy

Keyword(s):

Reynolds Number ◽

Lift Coefficient ◽

Angle Of Attack ◽

Reynolds Numbers ◽

Low Reynolds Numbers ◽

Critical Range ◽

Gurney Flap ◽

Stall Angle ◽

Lift And Drag ◽

Naca 0012

Steady state, two-dimensional computational investigations performed on NACA 0012 airfoil to analyze the effect of variation in Reynolds number on the aerodynamics of the airfoil without and with a Gurney flap of height of 3% chord are presented in this paper. RANS based one-equation Spalart-Allmaras model is used for the computations. Both lift and drag coefficients increase with Gurney flap compared to those without Gurney flap at all Reynolds numbers at all angles of attack. The zero lift angle of attack seems to become more negative as Reynolds number increases due to effective increase of the airfoil camber. However the stall angle of attack decreased by 2° for the airfoil with Gurney flap. Lift coefficient decreases rapidly and drag coefficient increases rapidly when Reynolds number is decreased below critical range. This occurs due to change in flow pattern near Gurney flap at low Reynolds numbers.

Numerical Investigation of Flow past a Wavy Airfoil

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.110-116.4269 ◽

2011 ◽

Vol 110-116 ◽

pp. 4269-4275

Author(s):

K. Lam ◽

Y.F. Lin ◽

Y. Liu ◽

L. Zou

Keyword(s):

Numerical Investigation ◽

Lift Coefficient ◽

Angle Of Attack ◽

Large Eddy Simulations ◽

Wavy Surface ◽

Naca0012 Airfoil ◽

Large Eddy ◽

Stall Angle ◽

Coefficient Reduction

The effect of the wavy surface on the aerodynamic characteristics of an airfoil is studied using the large eddy simulations. A more gentle lift characteristic is obtained during stall. For angles of attack less than the baseline stall angle of a NACA0012 airfoil, a lift coefficient reduction was observed for the wavy airfoils, while the lift coefficient increases up to 23% greater than that of a NACA0012 airfoil when the angle of attack is larger than the baseline stall angle of the NACA0012 airfoil.

Lift and Drag Coefficient Map of NACA4415 Airfoil

10.1088/1742-6596/2076/1/012066 ◽

2021 ◽

Vol 2076 (1) ◽

pp. 012066

Author(s):

Rui Yin ◽

Jing Huang ◽

Zhi-Yuan He

Keyword(s):

Reynolds Number ◽

Drag Coefficient ◽

Lift Coefficient ◽

Angle Of Attack ◽

Optimal Angle ◽

Fluent Software ◽

Lift And Drag ◽

Drag Ratio ◽

Lift To Drag Ratio

Abstract The NACA4415 airfoil was numerically simulated with the help of the Fluent software to analyze its aerodynamic characteristics. Results are acquired as follows: The calculation accuracy of Fluent software is much higher than that of XFOIL software; the calculation result of SST k-ω(sstkw) turbulence model is closest to the experimental value; within a certain range, the larger the Reynolds number is, the larger the lift coefficient and lift-to-drag ratio of the airfoil will be, and the smaller the drag coefficient will be; when the angle of attack is less than the optimal angle of attack, the Reynolds number has less influence on the lift-to-drag coefficient and the lift-to-drag ratio; as the Reynolds number increases, the optimal angle of attack increases slightly, and the applicable angle of attack range for high lift-to-drag ratios becomes smaller.

Effects of Pitching Motion Elements on Aerodynamic Characteristics of Airfoil

10.1088/1742-6596/2076/1/012078 ◽

2021 ◽

Vol 2076 (1) ◽

pp. 012078

Author(s):

Rui Yin ◽

Jing Huang ◽

Zhi-Yuan He

Keyword(s):

Drag Coefficient ◽

Lift Coefficient ◽

Angle Of Attack ◽

Initial Angle ◽

Pitching Motion ◽

The Difference ◽

Lift And Drag ◽

Drag Ratio ◽

Lift To Drag Ratio

Abstract The aerodynamic characteristics of NACA4412 airfoil with different pitching motion elements were compared and analyzed based on CFD in this research. The results are acquired as follows: the difference between the lift and drag coefficients of the airfoil during pitch up and pitch down motions becomes larger with the increase of the pitching amplitude or initial angle of attack; as the pitching amplitude increases, the lift coefficient grows slightly greater and the drag coefficient grows much greater; as the initial angle of attack increases, the lift coefficient grows much greater and the drag coefficient grows slightly; the smaller the attenuation frequency is, the larger the lift-to-drag ratio of the airfoil will be.

THE EFFECTS OF ANGLE OF ATTACK, REYNOLD NUMBERS AND WINGLET STRUCTURE ON THE PERFORMANCE OF CESSNA 172 SKYHAWK

Angkasa: Jurnal Ilmiah Bidang Teknologi ◽

10.28989/angkasa.v10i1.206 ◽

2018 ◽

Vol 10 (1) ◽

pp. 61

Author(s):

Henny Pratiwi

Keyword(s):

Wind Tunnel ◽

Drag Force ◽

Lift Coefficient ◽

Angle Of Attack ◽

Balsa Wood ◽

Wingtip Vortex ◽

The One ◽

Lift And Drag ◽

Drag Ratio ◽

Lift To Drag Ratio

This research aims to investigate the effects of angle of attack, Reynold numbers and winglet structure on the performance of Cessna 172 Skyhawk aircraft with winglets variation design. Winglets improve efficiency by diffusing the shed wingtip vortex, which reducing the drag due to lift and improving the wing’s lift over drag ratio. In this research, the specimens are the duplicated of Cesnna 172 Skyhawk wing with 1:40 ratio made of balsa wood. There are three different winglet designs that are compared with the one without winglet. The experiments are conducted in an open wind tunnel to measure the lift and drag force with Reynold numbers of 25,000 and 33,000. It can be concluded that the wings with winglets have higher lift coefficient than wing without winglet for both Reynold numbers. It was also found that all wings with winglets have higher lift-to-drag ratio than wings without winglet where the blended 45o cant angle has the highest value.

Numerical Study on Aerodynamic Characteristics of NACA0015

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.302.640 ◽

2013 ◽

Vol 302 ◽

pp. 640-645

Author(s):

Su Jeong Lee ◽

Eui Chul Jeong ◽

Hee Chang Lim

Keyword(s):

Pressure Distribution ◽

Numerical Study ◽

Lift Coefficient ◽

Angle Of Attack ◽

Vertical Axis ◽

Surface Pressure Distribution ◽

Maximum Value ◽

Stall Angle ◽

Near Wall

In this study, a numerical simulation is made to understand the effect of the angle of attack on a NACA airfoil, which will be used for a basic shape to apply for making the vertical axis Darius wind turbine. The near-wall y+ value which is less than 1 is known to be most desirable for a near-wall modeling. Therefore, this study is aiming to observe the variation and find the optimized value of y+. The Reynolds number used in this study was 360,000, where the chord length and the velocity were 0.12m and 43.8m/s, respectively. Generally, the lift coefficient of the airfoil tends to increase as the angle of attack increases and it decreases substantially at the stall angle and then it decreases. As expected, the lift coefficient increases rapidly from 0 to 10° and then after the sudden drop of the lift (i.e., the stall) at around 10 to 16° depending on the y+ value. In this paper, it seems to be reliable and appropriate to use y+ value close to 1. From the surface pressure distribution, from the result obtained the ratio of pressure distribution of maximum value to the minimum value was 1.89and these peaks move forward to backward as the angle of attack increases.

Numerical Investigation of M21 Aerofoil and Effect of Plain Flapper at Various Angle of Attack

10.1088/1742-6596/2070/1/012153 ◽

2021 ◽

Vol 2070 (1) ◽

pp. 012153

Author(s):

Vimal Patel ◽

Vikram Rathod ◽

Chirag Patel

Keyword(s):

Drag Force ◽

Lift Force ◽

Lift Coefficient ◽

Angle Of Attack ◽

Similar Work ◽

Maximum Value ◽

Different Types ◽

Stall Angle ◽

Drag And Lift ◽

Plane Jet

Abstract The aerofoil plays an important role in any structure moving in a fluid-like in a passenger plane, jet plane, or helicopter. The aerofoils decide whether the lift force is appropriate to balance the weight of the plane or not and the amount of drag force is required on the vehicle. The purpose of this project is to simulate the M21 Aerofoil with the help of FLUENT and validate it with theory. This Project also includes the study of various Flapper designs and their simulation. Flappers are useful when the Airplane is about to take-off or landing. The Important parameters to be study are Lift Force, Drag Force, lift coefficient, and Drag coefficient. Simulation has been done for the different Angle of Attack which is useful for finding maximum Lift force and Stall Angle. The Work includes simulation of Plain Flapper for the Angle of Attack where CL/CD is maximum. Similar work can be done for different types of Flapper used in Airplane. The stall angle achieved for M21 was 24° and maximum value of CL/CD measured at 7° A.O.A. Investigation also shows that for the 10° plain flap angle highest drag and lift force was possible. It contains the study of the Adverse Yaw effect which rolls the Airplane while taking a turn. since the validity of any theoretical prediction can only be assessed in practice.

Numerical study of geometric morphing wings of the 1303 UCAV

The Aeronautical Journal ◽

10.1017/aer.2021.15 ◽

2021 ◽

pp. 1-17

Author(s):

B. Nugroho ◽

J. Brett ◽

B.T. Bleckly ◽

R.C. Chin

Keyword(s):

Flight Control ◽

Numerical Study ◽

Morphing Wing ◽

Rolling Moment ◽

Wide Range ◽

Morphing Wings ◽

Wing Geometry ◽

Lift And Drag ◽

Wing Morphing

ABSTRACT Unmanned Combat Aerial Vehicles (UCAVs) are believed by many to be the future of aerial strike/reconnaissance capability. This belief led to the design of the UCAV 1303 by Boeing Phantom Works and the US Airforce Lab in the late 1990s. Because UCAV 1303 is expected to take on a wide range of mission roles that are risky for human pilots, it needs to be highly adaptable. Geometric morphing can provide such adaptability and allow the UCAV 1303 to optimise its physical feature mid-flight to increase the lift-to-drag ratio, manoeuvrability, cruise distance, flight control, etc. This capability is extremely beneficial since it will enable the UCAV to reconcile conflicting mission requirements (e.g. loiter and dash within the same mission). In this study, we conduct several modifications to the wing geometry of UCAV 1303 via Computational Fluid Dynamics (CFD) to analyse its aerodynamic characteristics produced by a range of different wing geometric morphs. Here we look into two specific geometric morphing wings: linear twists on one of the wings and linear twists at both wings (wash-in and washout). A baseline CFD of the UCAV 1303 without any wing morphing is validated against published wind tunnel data, before proceeding to simulate morphing wing configurations. The results show that geometric morphing wing influences the UCAV-1303 aerodynamic characteristics significantly, improving the coefficient of lift and drag, pitching moment and rolling moment.