investigation of airfoil design using ansys. - ethesis - National

55 Pages·2014·2.82 MB·English

INVESTIGATION OF AIRFOIL DESIGN

A thesis Submitted by,

AVNISH KUMAR
(Roll: 110CE0444)

In partial fulfilment of the requirement
for the award of the degree
of

BACHELOR OF TECHNOLOGY
in
CIVIL ENGINEERING

Under the guidance of,
PROF. AWADESH KUMAR,
DEPARTMENT OF CIVIL ENGINEERING

NATIONAL INSTITUTE OF TECHNOLOGY ROURKELA

ROURKELA 769008, ODISHA, INDIA
NATIONAL INSTITUTE OF TECHNOLOGY, ROURKELA

CERTIFICATE

This is to certify that the Project Report entitled, “INVESTIGATION OF AIRFOIL

DESIGN” submitted by AVNISH KUMAR (Roll-110CE0444) and

in partial fulfilment for the requirements for the award of the Degree of Bachelor of

Technology in Civil Engineering at National Institute of Technology, Rourkela

(Deemed university) is an authentic work carried out by him under my supervision and

guidance. To the best of my knowledge, the matters embodied in the thesis have not

been submitted to any other university/Institute for the award of any Degree or

Diploma.

Prof. Awadesh kumar,
Department Of Civil Engineering,
Place: NIT Rourkela National Institute ofTechnology,
Date: Rourkela-769008, Orissa (India).

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ACKNOWLEDGEMENTS
.

I would like to express my deepest appreciation to my respectable guide Prof.

Awadesh kumar, an associate professor and our faculty advisor for his support,

guidance, care, tutelage, motivation and patience throughout the research period. I

appreciate his talent and the encouragement which he provided me throughout this

academic year. All credit goes to him who made my project successful. Without his

help and contribution my work would not have been able to come to this stage of

completeness and fulfilment of my bachelor degree.

Apart from him I would like to thank each and every faculties of my civil engineering

department for their knowledge, assistance, motivation and care throughout the study

period.

I also place on record, my sense of gratitude to one and all, who directly or indirectly,

have lent their hands in successful completion of this project work.
.

Avnish kumar
Roll No: 110ce0444
B.Tech Civil Engineering

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ABSTRACT

In this project titled “Investigation of airfoil design” an effort has been made to make a
detailed study on lift and drag coefficien of various airfoil sections. Airfoil is an
important part of any airplane structure whether it may be passenger planes, jet planes
or helicopters. The airfoils decide whether the lift force is sufficient to balance the
weight of the plane or not and how much drag force is being applied on the plane.
Airfoils are basically divided into two categories, I have tried to diffrenciate between
the two types i.e Symmetrical and Asymmetrical airoils on the basis of their lift and
drag coefficient’s variation with angle of attack, stall angle of attack and magnitude of
the coefficients. I have also modelled three commonly used airfoil sections namely
BOEING737, MIG21 and BELL 200XV which are of passenger, jet and helicopters
respectively and tried to study their lift and drag coefficients and the lift force.

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Contents

Certificate 1
Acknowledgements 2
Abstract 3
List of Figures 6
List of Tables 8
List of Graphs 9
1. INTRODUCTION 10
1.1 General 11
1.2 Objectives 12
1.3 Methodology 12
2. STUDY AREA 13
2.1 Aerodynamics 14
2.2 ANSYS 16
3. LITERATURE REVIEW 17
3.1 Literature review 18
4. INVESTIGATION OF SYMMETRIC AIRFOIL DESIGN 19
4.1 Modelling and Meshing 20
4.2 Pressure and velocity distribution 21
4.3 Results 23
5. INVESTIGATION OF ASYMMETRIC AIRFOIL DESIGN 25
5.1 Modelling and Meshing 26
5.2 Pressure and velocity distribution 27
5.3 Results 28
6. INVESTIGATION OF AIRFOIL DESIGN OF BOEING 737 30
6.1 Modelling and Meshing 31
6.2 Pressure and velocity distribution 32
6.3 Results 34
7. INVESTIGATION OF AIRFOIL DESIGN OF MIG 21 37
7.1 Modelling and Meshing 38
7.2 Pressure and velocity distribution 39
7.3 Results 40

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8. INVESTIGATION OF AIRFOIL DESIGN OF BELL 200XV 42
8.1 Modelling and Meshing 43
8.2 Pressure and velocity distribution 44
8.3 Results 45

9. ANALYSIS OF RESULTS 47
9.1 Symmetric vs. asymmetric 48
9.2 Comparison of boeing 737, mig 21 and bell 200xv 49
9.3 Velocity vs. Acceleration 50

10. CONCLUSION 52
10.1 Conclusion 53

REFERENCES 54.

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LIST OF FIGURES.

FIGURE TITLE PAGE
NO.
Fig. 1.1(a) Forces acting on an aeroplane. 11
Fig. 2.1(a) General section of an airfoil. 15
Fig. 4.1(a) Geometry of the symmetrical airfoil section. 20
Fig. 4.1(b) Meshing of air profile around the symmetrical airfoil. 20
Fig. 4.2(a) Pressure distribution around the symmetrical airfoil 21
at 0 Angle of attack.
o
Fig. 4.2(b) Pressure distribution around the symmetrical airfoil 21
at stall Angle of attack
Fig. 4.2(c) Contours of velocity magnitude in m/s at 0 angle of 22
0
attack
Fig. 4.2(d) Enlarged view of contours of velocity magnitude in 22
m/s at an angle of attack greater than stall angle of
attack
Fig. 5.1(a) Geometry of the Asymmetrical airfoil section. 26
Fig. 5.1(b) Close up of mesh around the asymmetrical airfoil. 26
Fig. 5.2(a) Contours of static pressure at 0 angle of attack for 27
o
asymmetrical airfoil.
Fig. 5.2(b) Contours of velocity magnitude at 0 angle of attack 27
o
for asymmetrical airfoil.
Fig. 6.1(a) Geometry of boeing 737 airfoil with air profile drawn 31
around it.
Fig. 6.1(b) Meshing of air profile around the boeing737 airfoil. 31
Fig. 6.2(a) Contours of static pressure for boeing 737 airfoil at 00 32

A.O.A.
Fig. 6.2(b) Contours of static pressure for boeing 737 airfoil at 32
stall A.O.A

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Fig. 6.2(c) Contours of velocity magnitude for boeing 737 airfoil 33
at 00A.O.A .

Fig. 6.2(d) Contours of velocity magnitude for boeing 737 airfoil 33
at stall A.O.A.
Fig. 7.1(a) Geometry of the MIG 21 Airfoil. 38
Fig 7.1(b) Close up of mesh drawn around the airfoil. 38
Fig. 7.2(a) Contours of static pressure for MIG21 airfoil at 0 39
0
A.O.A.
Fig. 7.2(b) Contours of veloity magnitude for MIG21 airfoil at 0 39
0
A.O.A.
Fig. 8.1(a) Geometry of the BELL 200XV Airfoil 43
Fig. 8.1(b) Meshing of the BELL 200XV Airfoil 43
Fig. 8.2(a) Contours of static pressure for BELL200 XV airfoil at 44
00 A.O.A.

Fig. 8.2(b) Contours of static pressure for BELL200 XV airfoil at 44
00 A.O.A.
Fig. 9.1(a) Comparison of lift coefficient between symmetric 48
and asymmetric Airfoil.
Fig. 9.1(b) Comparison of drag coefficient between symmetric 48
and asymmetric airfoil.

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List of tables

TABLE TITLE PAGE NO.
Variation of lift and drag coefficient with angle of 23

Table 4.3(a)
atack for symmetrical airfoil.
Variation of lift and drag coefficient with angle of

Table 5.3(a) 28
attack for asymmetrical airfoil.
Variation of lift and drag coefficient and lift force

Table 6.3(a) 34
with angle of attack for B737.
Variation of lift and drag coefficient with angle of

Table 7.3(a) 40
attack for MIG 21.
Variation of lift and drag coefficient with angle of

Table 8.3(a) 45
attack for BELL 200 XV.
Vertical accelration vs. horizontal velocity for

Table 9.3(a) 50
B737 at stall angle of attack.
Vertical accelration vs. horizontal velocity for

Table 9.3(c) 51
MIG21 at stall angle of attack.

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List of graph
GRAPH TITLE PAGE NO.
Graph 4.3(b) Variation of lift coefficient with angle of attack 24
of Symmetrical airfoil.
Graph 4.3(c) Variation of drag coefficient with angle of 24
attack for symmetrical airfoil.
Graph 5.3(b) Variation of lift coefficient with angle of attack 29
for asymmetrical airfoil.
Graph 5.3(c) Variation of drag coefficient with angle of 29
attack for asymmetrcal airfoil.
Graph 6.3(b) Variation of lift coefficient with angle of attack 35
for BOEING 737 Airfoils.
Graph 6.3(c) Variation of drag coefficient with angle of 35
attack for BOEING 737 Airfoils.
Graph 6.3(d) Variation of lift force with angle of attack for 36
BOEING 737 Airfoils.
Graph 7.3(b) Variation of lift coefficient with angle of attack 41
for MIG21 Airfoils.
Graph 7.3(c) Variation of drag coefficient with angle of 41
attack for MIG21 Airfoils.
Graph 7.3(d) Variation of lift force with angle of attack for 41
MIG21 Airfoils.
Graph 8.3(b) Variation of lift coefficient with angle of attack 46
for BELL 200XV Airfoils.
Graph 8.3(c) Variation of drag coefficient with angle of 46
attack for BELL 200XV Airfoils.
Graph 8.3(d) Variation of drag coefficient with angle of 46
attack for BELL 200XV Airfoils.
Graph 9.2(a) Comparison of lift coefficient vs. Angle of 49
attack.
Graph 9.2(b) Comparison of drag coefficient vs. Angle of 49
attack.
Graph 9.2(c) Comparison of lift force vs. Angle of attack. 49
Graph 9.3(b) Vertical accelration vs. horizontal velocity for 50
B737 at stall angle of attack.
Graph 9.3(d) Vertical accelration vs. horizontal velocity for 51
MIG21 at stall angle of attack.

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