1) A wind tunnel test was conducted on a baseline NACA 0015 airfoil model to measure aerodynamic characteristics at different angles of attack from 0 to 20 degrees.
2) The lift coefficient was found to be a maximum of 1.3 at 10 degrees angle of attack, while the drag coefficient reached a maximum of 0.31 at 25 degrees.
3) Flow separation was observed to begin occurring between 15-20 degrees angle of attack based on pressure measurements and flow visualization. The optimal angle of attack was approximately 12 degrees.
To theoretically analyze the effects of Angle of Attack on Pressure Difference on airfoil.
To suggest the best port location on different airfoils, in order to install Pressure Differential Angle of Attack measuring instrument on them
This presentation is made to explain the best port locations on various 2D geometries to measure Angle of Attack as a function of Pressure Differential
To theoretically analyze the effects of Angle of Attack on Pressure Difference on airfoil.
To suggest the best port location on different airfoils, in order to install Pressure Differential Angle of Attack measuring instrument on them
This presentation is made to explain the best port locations on various 2D geometries to measure Angle of Attack as a function of Pressure Differential
The flow across an airfoil is studied for different angle of attack. The CFD analysis results are documented and studied for different angle of attack using fluent & gambit.
Design and Fabrication of Subsonic Wind TunnelIJMERJOURNAL
ABSTRACT: A Wind Tunnel is a tool used in aerodynamic research to study the effects of air moving past the solid objects. Wind tunnels were first as a means of studying vehicles (primarily airplanes) in free flight. A Wind tunnel is used to find the aerodynamics and also to measure drag and down force of airfoils. The wind tunnel is composed of a contraction cone, test section and diffuser, with nessary instrumentation to measure the drag and downforce acting on the vehicles. Our project aims at using hand fabricated wind tunnel to test aerodynamics of scaled models and also to calculate the drag in them. It is very important nowadays to consider the aerodynamics of any vehicles whiles designing, this helps in improving the efficiency and reduces the fuel consumption. With this hand fabricated wind tunnel it makes the checking of aerodynamics and calculation of drag for scaled models very easy. This reduces the time taken for designing and production
Naca 2415 finding lift coefficient using cfd, theoretical and javafoileSAT Journals
Abstract In this paper we have studied the experimental characteristic graph of NACA 2415.The experimental graphs were taken from the book, “Theory of wing section” by IRA H. ABBOTT. We used these graphs for the validation of our results. Then we use CFD to simulate the experimental flow conditions and check the results and compare them with the experimental results. We meshed the airfoil in ICEM CFD so that the meshing is very precise. We then calculate the NACA 2415 airfoil’s lift at different angle of attack theoretically and using CFD analysis and compare them with the experimental values. We find the errors between experimental and CFD values as well as experimental and theoretical values. We used another simulation software called Javafoil and used it for comparison. Keywords: Experimental, CFD, Theoretical, Javafoil
Design Analysis Of Uav (Unmanned Air Vehicle) Using NACA 0012 Aerofoil ProfileDr. Bhuiyan S. M. Ebna Hai
This research work is concerned with the application of conceptual design of Unmanned Air Vehicle (UAV). UAV is used for surveillance and reconnaissance to serve for the defense as well as national security and intelligence purpose. Here NACA 0012 aerofoil profile is used to design UAV by using CFD (Computational Fluid Dynamics) software. The aim of this research is to investigate the flow patterns and determine the aerodynamic characteristics of NACA 0012 profile by varying the angle of attack and Reynolds Number numerically. The research is carried out with symmetric aerofoil with the chord length of 0.1m. The research work explained different aerodynamic characteristics like lift force and drag force, lift and drag coefficient, pressure distribution over aerofoil etc.
This report is a simulation for a flow over an airfoil "NACA 0009" at Reynolds number equals 1 million for four angles of attack using three different turbulence models and of cause a grid independence solution.
The goal of this study is to apply the knowledge obtained from studying in the university and self-learning in order to solve a specific task of finding the coefficient of drag and lift for the airfoil.
A youtube video made by me explaining how to simulate a flow over an airfoil: https://goo.gl/9VYRFM
Team members:
Ahmed Kamal Shalaby
Ahmed Gaber Ahmed
Esraa Mahmoud Saleh
Study on Effect of Semi Circular Dimple on Aerodynamic Characteristics of NAC...ROSHAN SAH
This is the research paper that was published in the AIP Conference Proceedings this year. This paper contains the new modification design in NACA 2412 airfoil and different aerodynamics characteristics were determined and compared with the basic airfoil and multiple conclusion were made for the results.
This was actually my B.Tech. min project work back on 2016 Nov end.
The flow across an airfoil is studied for different angle of attack. The CFD analysis results are documented and studied for different angle of attack using fluent & gambit.
Design and Fabrication of Subsonic Wind TunnelIJMERJOURNAL
ABSTRACT: A Wind Tunnel is a tool used in aerodynamic research to study the effects of air moving past the solid objects. Wind tunnels were first as a means of studying vehicles (primarily airplanes) in free flight. A Wind tunnel is used to find the aerodynamics and also to measure drag and down force of airfoils. The wind tunnel is composed of a contraction cone, test section and diffuser, with nessary instrumentation to measure the drag and downforce acting on the vehicles. Our project aims at using hand fabricated wind tunnel to test aerodynamics of scaled models and also to calculate the drag in them. It is very important nowadays to consider the aerodynamics of any vehicles whiles designing, this helps in improving the efficiency and reduces the fuel consumption. With this hand fabricated wind tunnel it makes the checking of aerodynamics and calculation of drag for scaled models very easy. This reduces the time taken for designing and production
Naca 2415 finding lift coefficient using cfd, theoretical and javafoileSAT Journals
Abstract In this paper we have studied the experimental characteristic graph of NACA 2415.The experimental graphs were taken from the book, “Theory of wing section” by IRA H. ABBOTT. We used these graphs for the validation of our results. Then we use CFD to simulate the experimental flow conditions and check the results and compare them with the experimental results. We meshed the airfoil in ICEM CFD so that the meshing is very precise. We then calculate the NACA 2415 airfoil’s lift at different angle of attack theoretically and using CFD analysis and compare them with the experimental values. We find the errors between experimental and CFD values as well as experimental and theoretical values. We used another simulation software called Javafoil and used it for comparison. Keywords: Experimental, CFD, Theoretical, Javafoil
Design Analysis Of Uav (Unmanned Air Vehicle) Using NACA 0012 Aerofoil ProfileDr. Bhuiyan S. M. Ebna Hai
This research work is concerned with the application of conceptual design of Unmanned Air Vehicle (UAV). UAV is used for surveillance and reconnaissance to serve for the defense as well as national security and intelligence purpose. Here NACA 0012 aerofoil profile is used to design UAV by using CFD (Computational Fluid Dynamics) software. The aim of this research is to investigate the flow patterns and determine the aerodynamic characteristics of NACA 0012 profile by varying the angle of attack and Reynolds Number numerically. The research is carried out with symmetric aerofoil with the chord length of 0.1m. The research work explained different aerodynamic characteristics like lift force and drag force, lift and drag coefficient, pressure distribution over aerofoil etc.
This report is a simulation for a flow over an airfoil "NACA 0009" at Reynolds number equals 1 million for four angles of attack using three different turbulence models and of cause a grid independence solution.
The goal of this study is to apply the knowledge obtained from studying in the university and self-learning in order to solve a specific task of finding the coefficient of drag and lift for the airfoil.
A youtube video made by me explaining how to simulate a flow over an airfoil: https://goo.gl/9VYRFM
Team members:
Ahmed Kamal Shalaby
Ahmed Gaber Ahmed
Esraa Mahmoud Saleh
Study on Effect of Semi Circular Dimple on Aerodynamic Characteristics of NAC...ROSHAN SAH
This is the research paper that was published in the AIP Conference Proceedings this year. This paper contains the new modification design in NACA 2412 airfoil and different aerodynamics characteristics were determined and compared with the basic airfoil and multiple conclusion were made for the results.
This was actually my B.Tech. min project work back on 2016 Nov end.
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
Fluid-Structure Interaction Over an Aircraft WingIJERDJOURNAL
ABSTRACT:- Aircraft is a brilliant man-made structure which helps us to fly over the world. At the same time, aircraft is a complex structure to be checked and maintained for the aero elasticity due to aerodynamic properties. In this paper, the fluid-structure interaction problem in super critical NASA SC(2)-0412 airfoil is discussed. The main aim of this project is to find the best performance and deformation limit of the wing on different Mach numbers. This project is completely done by numerical methods of designing the wing using CATIA and flow properties in Computational Fluid Dynamics (CFD) method. Finally, the structural analysis for deformation is analysed in ANSYS. The analytical approach of fluid-structure interaction over an Aircraft wing is complex.
COMPUTATIONAL FLUID DYNAMIC ANALYSIS OF AIRFOIL NACA0015IAEME Publication
In this chapter we choose standard airfoil NACA 0015. Which is symmetrical airfoil with a 15%thickness to chord ratio was analyzed on ANSYS FLUENT to determine the coefficient of lift,
coefficient of drag and graph of coefficient of lift vs. coefficient of drag. The 2-dimensional crosssectional view was considered. The wind velocity was taken as 17m/s which arecorresponding to232,940 Reynolds number. The airfoil, with an 8 in chord, was analyzed at 0, 5, 10 and 15 degrees.
Parameters viz. Coefficient of lift (Cl), Coefficient of drag (Cd) nd Cl/Cd are calculated and areplotted against different angle of attack.
COMPUTATIONAL FLUID DYNAMIC ANALYSIS OF NACA 0006 AEROFOIL AT DIFFERENT PARAM...
M0401091096
1. American Journal of Engineering Research (AJER) 2015
w w w . a j e r . o r g Page 91
American Journal of Engineering Research (AJER)
e-ISSN: 2320-0847 p-ISSN : 2320-0936
Volume-4, Issue-1, pp-91-96
www.ajer.org
Research Paper Open Access
Experimental Evaluation of Aerodynamics Characteristics of a
Baseline Airfoil
1,
Md. Rasedul Islam, 2,
Md. Amzad Hossain, 3,
Md. Nizam Uddin and
4,
Mohammad Mashud
1,2,3,4,
Department of Mechanical Engineering, Khulna University of Engineering & Technology (KUET),
Bangladesh
ABSTRACT : A wind tunnel test of baseline airfoil NACA 0015 model was conducted in the Wind tunnel wall
test section of the Department of Mechanical Engineering at KUET, Bangladesh . The primary goal of the test
was to measure airfoil aerodynamic characteristics over a wide range of Angle of Attack (AOA) mainly from
Zero degree to 20 degree AOA and with a wind tunnel fixed free stream velocity of 12m/s and at Re = 1.89×105
.
The pressure distribution in both upper and lower camber surface was calculated with the help of digital
pressure manometer. After analysis the value of Cl and Cd was found around 1.3 and 0.31 respectively.
KEYWORDS: Base line airfoil NACA 0015, Wind tunnel test, Aerodynamic Characteristics, AOA, Reynolds
Number
I. INTRODUCTION
The cross-sectional shape obtained by the intersection of the wing with the perpendicular plane is
called an airfoil. The camber, the shape of the mean camber line, and to a lesser extent, the thickness distribution
of the airfoil essentially controls the lift and moment characteristics of the airfoil [1]. Symmetric airfoils are
used in many applications including aircraft vertical stabilizers, submarine fins, rotary and some fixed wings
[2][3]. Here in this paper the chosen airfoil was tested to find the reliability of aerodynamics characteristics and
to understand the nature of difficulties arises in a newly setup wind tunnel [4][5]. This evaluation of
aerodynamic properties is measured and recorded so that future research work on active flow separation control
especially by CFJ method will be convenient and comparable to each other but it’s not our concern now [6]. The
Chosen Aerofoil NACA 0015 model has chord length of 30 cm and span of 50 cm and pressure were measured
at 31 point along chord length in each camber surface by digital pressure manometer with a free stream of
velocity 12m/s. Once getting pressure distribution, all other propertied like Coefficient of pressure Cp, lift
Coefficient Cl, Drag coefficient Cd, Drag Polar, Cl/ Cd were also calculated.
II. MODEL CONSTRUCTION AND METHODOLOGY
Designing NACA 0015 model by using surface profile equations.
For NACA 0015, Chord of the airfoil, c= 0.3 m
Maximum wing thickness, t= last two digit × % c=15× ×0.3 =0.04
Maximum camber, m= first digit × % c = 0 × × 0 = 0
Distance from leading edge to maximum wing thickness, p= second digit×10% c
= 0× × 0.3 = 0
Maximum wing thickness,
The mean chamber line,
For 0 < x < p
And,
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For p ≤ x ≤ c
And,
Now, coding a C-program including above equation and the upper and lower surface equation and after
compiling this program, a set of data were measured for the desired airfoil [7]. Plotting these data on any data
plotting software gives the profile like below:
Fig.1: NACA 0015 airfoil profile Fig.2: 3D Model view of Airfoil NACA 0015
After the construction, model were placed on an open loop Aerolab wind tunnel having test section geometry
of 1m x 1m and has an operating speed from 0-40 m/s (0-145 miles per hour). This is made possible by a 10-
horse power motor that drives a fan. After applying free stream velocity of 12 m/s, the value of pressure and
hence the value of Cp also calculated at different AOA. AOA has changed manually by a clamp hooked
assembly passing through the test wall section having a proper calibration of angle [8]. Following is the
schematic view of total setup:
Fig.3: Schematic view of wind tunnel setup where test was conducted.
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III. Figures and Tables
At AOA = 05 deg., 12 deg., 20 deg; the following value of Cp was witnessed.
Fig.4: -Cp vs. x/c at AoA= 05 deg.
From Fig.4 we can see that the stagnation point is indeed on the underside of the wing very near the front
at . There are no flat areas of Cp which indicates that there is no boundary layer separation. The pressure
distribution shows a smooth variation in both upper camber surface and lower camber surface. The maximum
value of -Cp in Baseline Airfoil are 1.5 and 0.25 at upper camber surface and lower camber surface respectively.
Fig.5: -Cp vs. x/c at AoA= 12 deg.
From Fig.5 we can see that the stagnation point is indeed on the underside of the wing very near the front
at . There are no flat areas of Cp which indicates that there is no boundary layer separation. The
maximum value of -Cp in Baseline Airfoil are 2.0 and 0.20 at upper camber surface and lower camber surface
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respectively. Since the value of pressure coefficient is increased this indicates that with further increase in AOA,
the pressure in upper camber surface will be detached from the wall hence will offer boundary layer separation.
Fig.6: -Cp vs. x/c at AoA= 20 deg.
From Fig.6 it seems that the value of Cp is smooth but at this stage boundary layer separation is occurred and
the value of drag coefficient is increased with a plunged in lift coefficient.
The following table shows the value of Cl, Cd and Cl/Cd at different Angle of Attack (AOA) :
Angle of Attack(AOA) Cl Cd Cl/Cd
0 0.01 0.01 1
5 0.6 0.02 30
10 1.3 0.08 16.25
12 1 0.105 9.52
20 0.9 0.25 3.6
25 0.85 0.31 2.74
Table 1: values of Cl, Cd and Cl/Cd at different Angle of Attack (AOA) of an airfoil NACA 0015.
The profile of Cl Vs. AOA is given below:
Fig.7: Cl Vs. AOA
From Fig.7 It is clear that Cl)max = 1.3 at AOA = 10 deg.
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The profile of Cd Vs. AOA is given below:
Fig.8: Cd vs. AOA
From Fig.8 It is clear that the value of Cd is increased as the AOA is increased.
The profile of Cl/ Cd vs. AOA is given below:
Fig.9: Cl/ Cd vs. AOA
From Fig.9 It is clear that the maximum value of Cl/ Cd is 30 and is gradually decreased as the value of AOA is
increased.
The smoke flow visualization technique is used to observe the flow separation at different AOA. After 12
degree Angle of Attack the snap short of flow visualization is given below:
Fig 10: snap short of smoke flow visualization after 12 degree AOA.
6. American Journal of Engineering Research (AJER) 2015
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IV. CONCLUSION
The NACA 0015 airfoil was analyzed for the lift, drag and moment coefficients as planned. From this
subsonic wind tunnel test of an Airfoil NACA 0015 it is found that the boundary layer separation is occurred in
between 15-20degree AOA and the maximum value of Cl is 1.3 at AOA = 10 deg. and Cd) max = 0.31 at AOA =
25 deg. And this value of Cd is increased gradually with the increase in AOA. The optimum AOA of this NACA
0015 Airfoil is found to be around 12 deg. It is clear from this paper that boundary layer separation is not
controlled or delayed as well as aerodynamic characteristics in not easy to enhance with this type of
conventional way. With some modification, techniques like Active flow separation should be applied in future
work to enhance the aerodynamic characteristics.
V. Acknowledgements
The author is profoundly indebted to. Dr. Mohammad Mashud ,Professor and Ex- Head, Department
of Mechanical Engineering, Khulna University of Engineering & Technology(KUET), Bangladesh, for his
proper guidance, inspiration, suggestion and all kinds of supports in performing and completing the dissertation
works in time.
REFERENCES
[1] W. L. I. Sellers, B. A. Singer, and L. D. Leavitt, “Aerodynamics for Revolutionary Air Vehicles.” AIAA 2004-3785, June 2003.
[2] Haritonidis, J. H., “Wind Tunnels”. Aerospace Engineering, The Ohio State University, Columbus, 2008.
[3] Miller, S. D., “Wind Tunnels”. Aerospace Engineering, The Ohio State University, Columbus, 2008.
[4] Haritonidis, J. H., “Lift, Drag and Moment of a NACA 0015 Airfoil”. Aerospace Engineering, The Ohio State University,
Columbus, 2008.
[5] Gilat, Amos, and Vish Subramaniam. Numerical Methods for Engineers and Scientists: An Introduction with Applications Using
MATLAB. Hobeken, NJ: John Wiley & Sons, Inc., 2008.
[6] Anderson, John D., Jr. Fundamentals of Aerodynamics. Fourth Edition. Boston: McGraw-Hill, 2007.
[7] A.Jameson,L.Martinelli,and N. A.Pierce. Optimum aerodynamic design using the Navier –Stokes equation. Theorical and
Computational Fluid Dynamics, 10: 213–237, 1998.
[8] A.Seifert,A.Darabi,and I. Wygnanski. Delay of airfoil stall by periodic excitation. AIAA Journal, 33(4):691–707, July 1996.