Lift, Drag and Moment of a Naca 0015 Airfoil
LIFT, DRAG AND MOMENT OF A NACA 0015 AIRFOIL by Steven D. Miller
DEPARTMENT OF AEROSPACE ENGINEERING
THE OHIO STATE UNIVERSITY
28 MAYi 2008
ABSTRACT
A NACA 0015 symmetrical airfoil with a 15% thickness to chord ratio was analyzed to determine the lift, drag and moment coefficients. A 2D airfoil was placed in a low speed wind tunnel with pressure taps along its surface and a pitot probe downstream to measure the flow characteristics. The wind tunnel was operated at a nominal 17 m/s during the coefficient measurements, a Reynold's number of about
232,940. The airfoil, with an 8 in chord, was analyzed at 0, 5, 10 and 15 degree angles of attack. The phenomenon known as hysteresis with regards to stall conditions was also observed by varying the angle of attack and wind tunnel velocity. ii
TABLE OF CONTENTS
Page
List of Figures iv
List of Tables iv
Nomenclature v
Chapter
I. Introduction 1
II. Apparatus and Instrumentation 2
III.Experimental Procedure 4
IV. Analysis 5
V. Results and Discussion 7
VI. Conclusions 13
Appendix 14
References 18 iii LIST OF FIGURES
LIST OF TABLES iv Figure Page
1 NACA 0015 Airfoil Cross-section with Pressure Taps 2
2 Pressure Distribution at 0 Deg Angle of Attack 8
3 Pressure Distribution at 5 Deg Angle of Attack 9
4 Pressure Distribution at 10 Deg Angle of Attack 9
5 Pressure Distribution at 15 Deg Angle of Attack 10
6 Velocity Profile of the Downstream Wake 11
Tables Page
1 Lift, Drag and Moment Coefficients 12
LIST OF FIGURES
LIST OF TABLES iv Figure Page
1 NACA 0015 Airfoil Cross-section with Pressure Taps 2
2 Pressure Distribution at 0 Deg Angle of Attack 8
3 Pressure Distribution at 5 Deg Angle of Attack 9
4 Pressure Distribution at 10 Deg Angle of Attack 9
5 Pressure Distribution at 15 Deg Angle of Attack 10
6 Velocity Profile of the Downstream Wake 11
Tables Page
1 Lift, Drag and Moment Coefficients 12
INTRODUCTION
This experiment analyzes the NACA 0015 airfoil in a low
DEPARTMENT OF AEROSPACE ENGINEERING
THE OHIO STATE UNIVERSITY
28 MAYi 2008
ABSTRACT
A NACA 0015 symmetrical airfoil with a 15% thickness to chord ratio was analyzed to determine the lift, drag and moment coefficients. A 2D airfoil was placed in a low speed wind tunnel with pressure taps along its surface and a pitot probe downstream to measure the flow characteristics. The wind tunnel was operated at a nominal 17 m/s during the coefficient measurements, a Reynold's number of about
232,940. The airfoil, with an 8 in chord, was analyzed at 0, 5, 10 and 15 degree angles of attack. The phenomenon known as hysteresis with regards to stall conditions was also observed by varying the angle of attack and wind tunnel velocity. ii
TABLE OF CONTENTS
Page
List of Figures iv
List of Tables iv
Nomenclature v
Chapter
I. Introduction 1
II. Apparatus and Instrumentation 2
III.Experimental Procedure 4
IV. Analysis 5
V. Results and Discussion 7
VI. Conclusions 13
Appendix 14
References 18 iii LIST OF FIGURES
LIST OF TABLES iv Figure Page
1 NACA 0015 Airfoil Cross-section with Pressure Taps 2
2 Pressure Distribution at 0 Deg Angle of Attack 8
3 Pressure Distribution at 5 Deg Angle of Attack 9
4 Pressure Distribution at 10 Deg Angle of Attack 9
5 Pressure Distribution at 15 Deg Angle of Attack 10
6 Velocity Profile of the Downstream Wake 11
Tables Page
1 Lift, Drag and Moment Coefficients 12
LIST OF FIGURES
LIST OF TABLES iv Figure Page
1 NACA 0015 Airfoil Cross-section with Pressure Taps 2
2 Pressure Distribution at 0 Deg Angle of Attack 8
3 Pressure Distribution at 5 Deg Angle of Attack 9
4 Pressure Distribution at 10 Deg Angle of Attack 9
5 Pressure Distribution at 15 Deg Angle of Attack 10
6 Velocity Profile of the Downstream Wake 11
Tables Page
1 Lift, Drag and Moment Coefficients 12
INTRODUCTION
This experiment analyzes the NACA 0015 airfoil in a low