Aerodynamic Perform of Aircraft Propeller.
I/We* have read this thesis and from my/our* opinion this thesis
is sufficient in aspects of scope and quality for awarding Bachelor of Mechanical Engineering (Design & Innovation)
Signature : ………...
Supervisor Name : Mr. Ahmad Rivai
Date : ………...
Signature : ………...
Supervisor II Name : Mdm. Ernie Binti Mat Tokit
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AERODYNAMIC PERFORMANCE OF AIRCRAFT PROPELLER
MOHD MUHYIDDIN BIN MUSTAFA
This report is presented in
partial fulfillment of the requirements for the
Bachelor of Mechanical Engineering (Design & Innovation)
Faculty of Mechanical Engineering Universiti Teknikal Malaysia Melaka
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I hereby declare that this report entitled “Aerodynamics Performance of Aircraft Propeller” is the result of my own research except as cited in the references.
Signature : ………...
Author’s Name : Mohd Muhyiddin Bin Mustafa
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This thesis is dedicated to my parents, Siti Fatimah Binti Salleh and Mustafa Bin Ibrahim, my brothers, sisters, Noor Masnira Binti Muhammed Salleh and other
family members who provide a loving, caring, encouraging, and supportive atmosphere. These are characteristic that contribute to the environment that is
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ACKNOWLEDGEMENTS
Alhamdulillah and Thank to Allah S.W.T. with all gracious and merciful for giving me strength and ability to accomplish this project research successfully. I would like to express my gratitude to all those who gave me the possibility to complete this thesis. I am deeply indebted to my supervisor Mr. Ahmad Bin Rivai whose help, stimulating suggestions, encouragement and guidance helped me in all the time of research for and writing of this thesis.
I owe my deepest gratitude to Mr. Yehia Abdel Monem Ahmed Eldrainy, Department of Mechanical Power Engineering, Faculty of Engineering, Alexandria University (Egypt), PHD Student and Research Assistant in Gas Turbine Combustion, Department of Aeronautical Engineering, Faculty of Mechanical Engineering, Universiti Teknologi Malaysia, UTM (Malaysia). His support at all time encourage me in finishing this project.
I acknowledge the Assoc. Prof. Ir. Dr. Shuhaimi Mansor, Head of Aeronautics Laboratory, Assoc. Prof Dr. Tholudin Hj. Mat Lazim and Mr. Abdul Basid Abd. Rahman, Laboratory Engineer, Aeronautical Engineering Laboratory, Universiti Teknologi Malaysia for their kind guidance and technical support for this project.
I also would like to thanks to Mr. Shafizal Bin Mat, Head of Design & Innovation Department, Faculty of Mechanical Engineering as well as to all lectures of Faculty of Mechanical Engineering for all their assistances.
Finally, I would like to thanks to all my colleagues. I want to thank them for all their help, support, interest and valuable hints in completing this thesis. Especially, I would like to give my special thanks to my family whose patient love enabled me to complete this work.
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ABSTRACT
The objectives of the thesis are to determine the aerodynamics performance and aerodynamic load distribution of an aircraft propeller especially Lift and Drag forces. The propeller force provides thrust which is the force created aerodynamically to push the aircraft through the air. Thus, it is important to define the aerodynamics performance of the propeller. This project is carried out by two different approaches which are the Analytical approach and Computational Fluid Dynamic (CFD) simulation using Fluent 6.3 software. Analytical Method using Propeller Blade analysis is one of the most effective methodologies available for determining the Aerodynamic Performance especially Lift and Drag force of a propeller. While the Computational Fluid Dynamic simulation using Fluent CFD software is used to simulate and capturing the aerodynamics performance of the propeller. Through both methodologies, the aerodynamic performance of the propeller was analyzed and compared. Results obtained were tabulated and the corresponding graphs were plotted. Both methods suggest that the Lift and Drag force increase with the increasing of relative velocity. There are several factors that contribute to error between the Analytical method and CFD Simulation. In conclusion, the propeller has less efficiency since the ratio of lift to drag is smaller than recommended ratio which is more than 13 for optimal performance of the propeller.
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ABSTRAK
Objektif tesis ini adalah untuk mengenalpasti prestasi aerodinamik dan agihan beban aerodinamik sebuah kipas pesawat terutama daya angkat dan daya seretan. Daya kipas menghasilkan daya tujahan yang terhasil secara aerodinamik untuk menolak pesawat melalui udara. Oleh itu, adalah penting untuk mengenalpasti prestasi aerodinamik sesebuah kipas. Projek ini dilaksanakan dengan menggunakan dua kaedah iaitu kaedah Analitik dan Kaedah Dinamik Bendalir (CFD) menggunakan perisian Fluent 6.3. Kaedah Analitik menggunakan Analisis Bilah Kipas merupakan pengkaedahan yang paling efektif bersesuaian untuk mengenalpasti prestasi aerodinamik terutama daya angkat dan daya seretan. Manakala simulasi Kaedah Dinamik Bendalir menggunakan perisian Fluent CFD digunakan untuk mensimulasi dan mendapatkan prestasi aerodinamik sebuah kipas. Melalui kedua-dua kaedah ini, prestasi aerodinamik kipas dianalisa dan dibandingkan. Keputusan yang diperolehi dijadualkan dan graf yang berkaitan dilukis. Kedua-dua kaedah ini mencadangkan daya angkat dan daya seretan meningkat apabila halaju relatif meningkat. Terdapat beberapa faktor yang menyumbang kepada perbezaan antara kaedah analisis dan Simulasi CFD. Sebagai kesimpulan, Kecekapan Kipas pesawat adalah kurang kerana nisbah Daya Angkat kepada Daya Seretan lebih kecil dari nisbah yang disarankan iaitu lebih dari 13 untuk prestasi optimum Kipas pesawat.
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CONTENTS
CHAPTER SUBJECT PAGE
DECLARATION ii
DEDICATION iii
ACKNOWLEDGEMENT iv
ABSTRACT v
ABSTRAK vi
CONTENTS vii
LIST OF TABLES xii
LIST OF FIGURES xiv
LIST OF FORMULATIONS xvi
LIST OF ABBREVIATIONS LIST OF SYMBOLS
xvii xviii
CHAPTER I INTRODUCTION
1.1 Project Background 1.2 Problem Statement 1.3 Objectives
1.4 Scope of project 1.5 Summary
1 2 2 3 3
CHAPTER II LITERATURE REVIEW
2.1 Introduction
2.2 Introduction to Propeller
2.2.1 Historical Development of Propeller Theory
4 5
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CHAPTER SUBJECT PAGE
2.2.2 Airfoil Geometry Parameters 2.2.3 Propeller Airfoil Design
2.2.4 Airfoil Terms 2.3 NACA Airfoil Series 2.4 Concept of Aerodynamics
2.4.1 Aerodynamic Forces and Moments
2.4.1.1 Definition of Lift 2.4.1.2 Definition of Drag
2.4.2 Resultant Aerodynamic Forces on Propeller
2.4.3 Definition of Stall
2.5 Aerodynamic Characteristic of Propeller (Propeller Blade Analysis)
2.5.1 Downwash Angle, εb 2.5.2 Section Thrust and
Circumferential Force 2.5.3 Total Relative Airspeed 2.5.4 Axial and Circumferential
Component of Induced Velocity 2.5.5 Section Lift and Drag
2.5.6 Lift Across Span
2.5.7 Propeller Airfoil Requirement 2.6 Propeller Analysis Method
2.7 Computational Fluid Dynamic
2.7.1 Development of Computational Fluid Dynamic
2.7.2 CFD Simulation Software(Fluent) 2.7.3 CFD Process
2.7.4 CFD Simulation Procedures 2.7.5 Defining a Boundary Condition
6 8 8 11 13 14 15 16 16 18 19 20 20 21 21 22 23 24 24 26 26 28 28 30 34
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ix CHAPTER CHAPTER III SUBJECT METHODOLOGY PAGE
3.1 Introduction 3.2 Project Overview 3.3 Methodology
3.3.1 Propeller Model Xoar 32 x 20 (Pusher)
3.4 Analytical Methods
3.4.1 NACA 2412 Airfoil 3.4.2 Results
3.5 CFD Simulation
3.5.1 Fluent CFD Simulation Methodology
3.5.2 Creating Model and Domain 3.5.3 Solution Procedure Flow
3.5.4 Spalart Allmaras Turbulence Model
3.5.5 Flow Domain
3.5.6 Meshing and Size Function 3.5.7 Boundary Condition 3.6 Validation
3.6.1 Experimental Data 3.6.2 NACA0012 Geometry 3.6.3 Validation Model 3.6.4 CFD Result
3.6.5 Comparison of Simulation and Experiment Data 35 35 36 36 37 37 40 49 49 50 51 52 53 53 54 55 55 55 58 59 60
CHAPTER IV RESULTS
4.1 Computational Fluid Dynamic
Simulation (Model and Domain) 4.1.1 Grid Settings
4.1.2 General Simulation Parameter
61 62 63
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CHAPTER SUBJECT PAGE
4.2 Computational Fluid Dynamic Simulation Results
4.2.1 Total Force and Coefficient 4.2.1.1 Simulation 1
4.2.1.2 Simulation 2 4.2.1.3 Simulation 3 4.2.1.4 Simulation 4 4.2.1.5 Simulation 5 4.2.1.6 Simulation 6 4.2.2 Pressure Contours
4.2.3 Velocity Magnitude and Vector 4.2.4 Behaviors of Velocity Vector at
Different Propeller Section and Relative Airspeed
4.2.5 Behaviors of Total Pressure at Different Propeller Section and Relative Airspeed 64 64 64 65 65 66 66 67 67 70 72 74
CHAPTER V ANALYSIS AND DISCUSSION
5.1 Propeller Aerodynamic Performance 5.1.1 Lift and Drag Forces
5.1.2 Lift and Drag Coefficient 5.1.3 Lift/Drag Ratio
78 78 79 80 5.2 Aerodynamic Load Distribution on
Propeller
5.2.1 Pressure Distribution on the Blades
5.2.2 Lift Distribution on the Blade 5.3 Comparison of Analytical and
Simulation Result
81
81 81
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CHAPTER SUBJECT PAGE
CHAPTER VI CONCLUSION AND RECOMMENDATION
6.1 Conclusion 6.2 Recommendation
REFERENCES BIBLIOGRAPHY APPENDICES
83 84
86 88
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LIST OF TABLES
NO. TITLE PAGE
2.1 NACA Airfoils Series 12
3.1 Xoar 32 x 20 Geometry 36
3.2 2-D Panel Method Solution Test Parameters 38
3.3 Coefficient of Lift and Drag 39
3.4 Variation of Section Lift Force, to Relative Airspeed, 41 3.5 Variation of Section Drag Force, to Relative Airspeed, 41 3.6 Theoretical Result for Lift force across the propeller span for
10m/s relative airspeed at eleven sections 42
3.7 Theoretical Result for Lift force across the propeller span for
20m/s relative airspeed at eleven sections 43
3.8 Theoretical Result for Lift force across the propeller span for
30m/s relative airspeed at eleven sections 44
3.9 Theoretical Result for Lift force across the propeller span for
40m/s relative airspeed at eleven sections 45
3.10 Theoretical Result for Lift force across the propeller span for
50m/s relative airspeed at eleven sections 46
3.11 Theoretical Result for Lift force across the propeller span for
60m/s relative airspeed at eleven sections 47
3.12 Result of Theoretical calculation for Lift Force across Span at
Different Relative Airspeed 49
3.13 Experimental Data of Lift and Drag Coefficient 55
3.14 Detail Coordinate of the NACA0012 Geometry 57
3.15 Fluent Simulation Result 59
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NO. TITLE PAGE
4.1 General Simulation Parameters - Models 63
4.2 General Simulation Parameters – Zones 63
4.3 General Simulation Parameters – Air Properties 64
4.4 Inlet Parameter for Simulation 1 64
4.5 Result for Simulation 1 64
4.6 Inlet Parameter for Simulation 2 65
4.7 Result for Simulation 2 65
4.8 Inlet Parameter for Simulation 3 65
4.9 Result for Simulation 3 65
4.10 Inlet Parameter for Simulation 4 66
4.11 Result for Simulation 4 66
4.12 Inlet Parameter for Simulation 5 66
4.13 Result for Simulation 5 66
4.14 Inlet Parameter for Simulation 6 67
4.15 Result for Simulation 6 67
4.16 Variation of Total Pressure at Different Relative Airspeed 69 4.17 Variation of Velocity Magnitude at Different Relative Airspeed 70 4.18 Behaviors of Velocity Vector at different Section and Airspeed 72 4.19 Behaviors of Total Pressure at different Section and Airspeed 74
5.1 Ratio of CL/CD at Different Relative Airspeed 80 5.2 Percentage of Error between Analytical and CFD Simulation 82
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LIST OF FIGURES
NO. TITLE PAGE
2.1 Propeller Construction 7
2.2 Propeller Lay-Out 8
2.3 General Propeller Terms 9
2.4 Propeller Blade Angle 10
2.5 Static Pressure Distribution 15
2.6 Shear Stress Distribution 15
2.7 Resultant aerodynamic force and the components into which it splits 17
2.8 Stall Conditions 18
2.9 Section force and velocities acting on a rotating propeller blade 19
2.10 Elliptical Lift Distribution 23
3.1 Xoar 32 x 20 Propeller 36
3.2 NACA Airfoil Section Generator 37
3.3 2-D Panel Method Solution Software 39
3.4 Graph for Lift force across the propeller span for 10m/s relative airspeed 42 3.5 Graph for Lift force across the propeller span for 20m/s relative airspeed 43 3.6 Graph for Lift force across the propeller span for 30m/s relative airspeed 44 3.7 Graph for Lift force across the propeller span for 40m/s relative airspeed 45 3.8 Graph for Lift force across the propeller span for 50m/s relative airspeed 46 3.9 Graph for Lift force across the propeller span for 60m/s relative airspeed 47
3.10 Ellipse Nomenclature 48
3.11 CFD Simulation Flow Chart 50
3.12 Solution Procedure Flow 51
3.13 NACA 0012 Airfoil 58
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NO. TITLE PAGE
3.15 Velocity Vector for SIM 2 60
4.1 Simulation Flow Domain 62
4.2 Propeller Wall 62
4.3 Propeller in Flow Domain 63
4.4 Example: Contours of Total Pressure for Simulation 1 67 4.5 Example: Contours of Total Pressure for Simulation 1 (Blade Back) 68 4.6 Example: Contours of Total Pressure for Simulation 1 (Blade Face) 68 4.7 Graph of Total Pressure Acting on Propeller
at Different Relative Airspeed 69
4.8 Example: Velocity Vector for Simulation 1 70
4.9 Graph of Velocity Magnitude Acting at Propeller Wall
at Different Relative Airspeed 71
5.1 Graph of Lift and Drag Force versus Relative Airspeed 78 5.2 Graph of Lift and Drag Coefficient versus Relative Airspeed 79
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LIST OF FORMULATIONS
NO. TITLE PAGE
(1) Lift, Normal, and Axial Force Equation 17
(2) Drag, Normal, and Axial Force Equation 17
(3) Total Downwash Angle 20
(4) Section Thrust 20
(5) Circumferential Force 20
(6a) Total Relative Airspeed 21
(6b) Total Relative Airspeed 21
(7) Induced Velocity 21
(8) Axial Component of Induced Velocity 22
(9) Circumferential Component of Induced Velocity 22
(10) Downwash Angle 22
(11) Advance Angle 22
(12) Induced Angle 22
(13) Section lift at radius, r 22
(14) Local Section Drag at radius, r 23
(15) Lift across Span 23
(16) Reynolds Number 38
(17) Local Section Lift 40
(18) Local Section Drag 40
(19) Lift force Using the Elliptical Lift Distribution Approach 41
(20a) Ellipse area 48
(20b) Ellipse area 48
(20c) Modified Ellipse area 48
(21a) Formula for the NACA 00XX Shape 55
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LIST OF ABBREVIATIONS
A - Axial Force
CAD - Computer-aided Design CAE Computer-aided Engineering
CATIA - Computer Aided Three-Dimensional Interactive Application CFD - Computational Fluid Dynamic
CMM - Coordinate Measuring Machine
CTRM - Composites Technology Research Malaysia
D - Drag Force
GUI - Graphical User Interface
k - Number of Blade
L - Lift Force
M - Moment
N - Normal Force
NACA - National Advisory Committee for Aeronautics
r - Radial Distance
R - Resultant Aerodynamic Force/Freestream Velocity RANS - Reynolds-averaged Navier–Stokes Equations TUAV - Tactical Unmanned Aerial Vehicle
SIM - Simulation
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LIST OF SYMBOLS
α - Angle of Attack
β - Aerodynamic Pitch Angle
εb - Total Downwash Angle
ε∞ - Propeller’s Forward Motion Vb - Total Relative Airspeed V∞ - Relative Air Velocity
ω - Angular Velocity
cb - Local Section Chord Length
Cd - Drag coefficient
Cl - Lift coefficient
Re - Reynolds Number
ρ - Density
μ - Viscosity
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CHAPTER I
INTRODUCTION
1.1 Project Background
An Aircraft Propeller is one of the most common important parts in the aircraft. It is an airfoil section designed to generate an aerodynamic force. The propeller force provides thrust to push the aircraft through the air. Thrust is the component of the aerodynamic force that is parallel to the axis of rotation. A propeller achieves a specified level of thrust by giving a relatively small acceleration to a relatively large mass of air.
Maximizing thrust while minimizing the torque necessary to turn a propeller has becomes one of the most important aspects of good propeller design. The torque required to turn the propeller multiplied with the angular velocity is called the brake power. It is the power that must be supplied by the engine. The thrust developed by the propeller multiplied by the airspeed of the aircraft is called the propulsive power. This is the useful power that is provided to propel the aircraft forward against the airframe drag. The ratio of the propulsive power to the brake power for a propeller is called the propulsive efficiency which is one of important measure of propeller performance. The thrust developed by the propeller when the aircraft is not moving is called the static thrust. This thrust is important for a propeller to produces high static thrust in order to accelerate the aircraft during takeoff.
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2 In order to analyze the aerodynamic performance of the propeller, Computational Fluid Dynamic (CFD) software is used to simulate the fluid flow over a body to solve and analyze the aerodynamic properties of a body. While, analytical approach will be used to compare the result gather from CFD simulation.
1.2 Problem Statement
Aircraft propeller evaluation in terms of aerodynamic performance is a critical aspect in designing an aircraft propeller. Propeller used to generate thrust that pushes the aircraft through the air. Thus, it is important to determine the aerodynamic performance and the aerodynamic load distribution over the propeller body. Since the airframe of an aircraft is induced by the drag on the air, the propeller needs to provide enough thrust to overcome the drag. There are several tools and method that can be used to analyze the aerodynamic performance of an aircraft propeller such as the Computational Fluid Dynamic simulation.
1.3 Objectives
The objectives of this thesis are:
a) To determine aerodynamic performance of an aircraft propeller especially Lift and Drag forces using analytical and CFD approaches.
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3
1.4 Scope of Project
The scope of the project is focused on the aerodynamic performance of aircraft propeller. Research is made to understand the aircraft propeller in general. Computational Fluid Dynamics (CFD) software is used to analyze and simulate the propeller in terms of aerodynamic performance and aerodynamic load distribution. The result of manual calculation and CFD software is compared.
1.5 Summary
This chapter is introducing the project background and the objective of the project. In addition, the problem statement and scope of study also being clarify in order to limit the range of this project conduct.
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4
CHAPTER II
LITERATURE REVIEW
2.1 Introduction
This literature review explores the dominant themes includes study and research of published materials like journals, thesis, case study, technical document, and online library. Generally, the purpose of a review is to analyze critical segment of a published body of knowledge through summary, classification and comparison of prior research studies, reviews of literature, and theoretical articles.
This chapter describes topics that related to propeller aerodynamics such as propeller theory, propeller geometry and parameters, aerodynamics forces and Computational Fluid Dynamic. Emphasize is more on aerodynamics force on the propeller blade and also the computational fluid dynamic approach and simulation.
Propeller is focused more on the definition of that phase, the historical development of propeller, the parameter governing propeller design, and the available propeller airfoil. Moreover, the Aerodynamic force will describe about the forces acting on the propeller and its analytical approach.
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5
2.2 Introduction to Propeller
The airplane propeller consists of two or more blades and a central hub to which the blades are attached. Each blade of an airplane propeller is essentially a rotating wing. As a result of their construction, the propeller blades are like airfoils and produce forces that create the thrust to pull, or push, the airplane through the air.
The power needed is supplied by the engine to rotate the propeller blades. The engine rotates the airfoils of the blades through the air at high speeds, and the propeller transforms the rotary power of the engine into forward thrust. As the air flows past the propeller, the pressure on one side of propeller is less than that on the other. As in a wing, this produces a reaction force in the direction of the lesser pressure. Propeller is mounted in a vertical plane, the area of lower pressure is in front of the propeller. Thus the thrust force is created in a forward direction.
Drag force that oppose the forward motion of an aircraft will be created as it moving through the air. Consequently, if an aircraft fly, there must be a force applied to it that is equal to the drag force, but acting in opposite direction. This force is called as the "thrust."
2.2.1 Historical Development of Propeller Theory
Development of a rational propeller theory begins with the work of Rankine and Froude with their interest in moving propulsion, but the fundamental principle is the same for water and air. They developed the fundamental momentum relation governing a propulsive device in fluid medium. (Wald Q. R, 2006)
Dvzewiercki (1892) develop the theory of propeller action where blade element were considered as individual lifting surface moving through medium on a helical path. In this
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LIST OF SYMBOLS
α - Angle of Attack
β - Aerodynamic Pitch Angle
εb - Total Downwash Angle
ε∞ - Propeller’s Forward Motion Vb - Total Relative Airspeed
V∞ - Relative Air Velocity
ω - Angular Velocity
cb - Local Section Chord Length
Cd - Drag coefficient
Cl - Lift coefficient
Re - Reynolds Number
ρ - Density
μ - Viscosity
(2)
CHAPTER I
INTRODUCTION
1.1 Project Background
An Aircraft Propeller is one of the most common important parts in the aircraft. It is an airfoil section designed to generate an aerodynamic force. The propeller force provides thrust to push the aircraft through the air. Thrust is the component of the aerodynamic force that is parallel to the axis of rotation. A propeller achieves a specified level of thrust by giving a relatively small acceleration to a relatively large mass of air.
Maximizing thrust while minimizing the torque necessary to turn a propeller has becomes one of the most important aspects of good propeller design. The torque required to turn the propeller multiplied with the angular velocity is called the brake power. It is the power that must be supplied by the engine. The thrust developed by the propeller multiplied by the airspeed of the aircraft is called the propulsive power. This is the useful power that is provided to propel the aircraft forward against the airframe drag. The ratio of the propulsive power to the brake power for a propeller is called the propulsive efficiency which is one of important measure of propeller performance. The thrust developed by the propeller when the aircraft is not moving is called the static thrust. This thrust is important for a propeller to produces high static thrust in order to accelerate the aircraft during takeoff.
(3)
Dynamic (CFD) software is used to simulate the fluid flow over a body to solve and analyze the aerodynamic properties of a body. While, analytical approach will be used to compare the result gather from CFD simulation.
1.2 Problem Statement
Aircraft propeller evaluation in terms of aerodynamic performance is a critical aspect in designing an aircraft propeller. Propeller used to generate thrust that pushes the aircraft through the air. Thus, it is important to determine the aerodynamic performance and the aerodynamic load distribution over the propeller body. Since the airframe of an aircraft is induced by the drag on the air, the propeller needs to provide enough thrust to overcome the drag. There are several tools and method that can be used to analyze the aerodynamic performance of an aircraft propeller such as the Computational Fluid Dynamic simulation.
1.3 Objectives
The objectives of this thesis are:
a) To determine aerodynamic performance of an aircraft propeller especially Lift and Drag forces using analytical and CFD approaches.
(4)
1.4 Scope of Project
The scope of the project is focused on the aerodynamic performance of aircraft propeller. Research is made to understand the aircraft propeller in general. Computational Fluid Dynamics (CFD) software is used to analyze and simulate the propeller in terms of aerodynamic performance and aerodynamic load distribution. The result of manual calculation and CFD software is compared.
1.5 Summary
This chapter is introducing the project background and the objective of the project. In addition, the problem statement and scope of study also being clarify in order to limit the range of this project conduct.
(5)
CHAPTER II
LITERATURE REVIEW
2.1 Introduction
This literature review explores the dominant themes includes study and research of published materials like journals, thesis, case study, technical document, and online library. Generally, the purpose of a review is to analyze critical segment of a published body of knowledge through summary, classification and comparison of prior research studies, reviews of literature, and theoretical articles.
This chapter describes topics that related to propeller aerodynamics such as propeller theory, propeller geometry and parameters, aerodynamics forces and Computational Fluid Dynamic. Emphasize is more on aerodynamics force on the propeller blade and also the computational fluid dynamic approach and simulation.
Propeller is focused more on the definition of that phase, the historical development of propeller, the parameter governing propeller design, and the available propeller airfoil. Moreover, the Aerodynamic force will describe about the forces acting on the propeller and its analytical approach.
(6)
2.2 Introduction to Propeller
The airplane propeller consists of two or more blades and a central hub to which the blades are attached. Each blade of an airplane propeller is essentially a rotating wing. As a result of their construction, the propeller blades are like airfoils and produce forces that create the thrust to pull, or push, the airplane through the air.
The power needed is supplied by the engine to rotate the propeller blades. The engine rotates the airfoils of the blades through the air at high speeds, and the propeller transforms the rotary power of the engine into forward thrust. As the air flows past the propeller, the pressure on one side of propeller is less than that on the other. As in a wing, this produces a reaction force in the direction of the lesser pressure. Propeller is mounted in a vertical plane, the area of lower pressure is in front of the propeller. Thus the thrust force is created in a forward direction.
Drag force that oppose the forward motion of an aircraft will be created as it moving through the air. Consequently, if an aircraft fly, there must be a force applied to it that is equal to the drag force, but acting in opposite direction. This force is called as the "thrust."
2.2.1 Historical Development of Propeller Theory
Development of a rational propeller theory begins with the work of Rankine and Froude with their interest in moving propulsion, but the fundamental principle is the same for water and air. They developed the fundamental momentum relation governing a propulsive device in fluid medium. (Wald Q. R, 2006)
Dvzewiercki (1892) develop the theory of propeller action where blade element were considered as individual lifting surface moving through medium on a helical path. In this