Pressure Distribution and Lift on a Piercy Aerofoil
Queen Mary, University of London
School of Engineering and Materials Science
Den233
Low Speed Aerodynamics
Pressure Distribution and Lift on a Piercy Aerofoil
Abstract
In this experiment in a low speed flow the static pressure around an aerofoil will be observed and discussed. The lift on the aerofoil will also be calculated and compared with the theoretical value. The aerofoil being used in this particular experiment is symmetrical and is taking place in a wind tunnel with a speed of 18.5m/s, therefore the flow is assumed to be incompressible. The different pressures along the surface of the aerofoil will be measured at an angle of attack of 4.1 degrees and 6.2 degrees. These values of pressure will then be analysed and graphs and calculations will be produced, the lift being calculated using the trapezium method in excel and these values and graphs will then be compared to the theoretical results for an inviscid flow from the thin aerofoil theory. The errors in the experiment will be quantified and any improvements to the experiment will be discussed.
Table of Contents
1. Introduction
2. Experiment Description
3. Apparatus
4. Calculations and Results
5. Discussion
6. Conclusion
7. References
Introduction
The thin aerofoil theory is very useful as it relates values of lift to small angles of attack for aerofoils with low camber and thickness without taking into account the viscosity of the flow. The thin aerofoil theory assumes that the flow is 2 dimensional, inviscid and incompressible. It can be used to predict pressures and forces on very thin cambered surfaces with the thickness approaching zero, along with finding the lift. The assumptions for this theory is that the flow must be inviscid, two dimensional, incompressible,
School of Engineering and Materials Science
Den233
Low Speed Aerodynamics
Pressure Distribution and Lift on a Piercy Aerofoil
Abstract
In this experiment in a low speed flow the static pressure around an aerofoil will be observed and discussed. The lift on the aerofoil will also be calculated and compared with the theoretical value. The aerofoil being used in this particular experiment is symmetrical and is taking place in a wind tunnel with a speed of 18.5m/s, therefore the flow is assumed to be incompressible. The different pressures along the surface of the aerofoil will be measured at an angle of attack of 4.1 degrees and 6.2 degrees. These values of pressure will then be analysed and graphs and calculations will be produced, the lift being calculated using the trapezium method in excel and these values and graphs will then be compared to the theoretical results for an inviscid flow from the thin aerofoil theory. The errors in the experiment will be quantified and any improvements to the experiment will be discussed.
Table of Contents
1. Introduction
2. Experiment Description
3. Apparatus
4. Calculations and Results
5. Discussion
6. Conclusion
7. References
Introduction
The thin aerofoil theory is very useful as it relates values of lift to small angles of attack for aerofoils with low camber and thickness without taking into account the viscosity of the flow. The thin aerofoil theory assumes that the flow is 2 dimensional, inviscid and incompressible. It can be used to predict pressures and forces on very thin cambered surfaces with the thickness approaching zero, along with finding the lift. The assumptions for this theory is that the flow must be inviscid, two dimensional, incompressible,
References: [1] Queen Mary University of London, DEN233, Low Speed Aerodynamics, Lab Handout, November 2013, (Accessed on 13th November 2013) [2] Queen Mary University of London, DEN233, Low Speed Aerodynamics, Lecture Notes, 2013, (Accessed on 13th November 2013)