PRESENTATION OUTLINE Experiment Objective Introduction Data Conclusion Recommendations

OBJECTIVE The purpose of this experiment is to define the parameters necessary to specify a NACA airfoil model.

INTRODUCTION Aerodynamics is the study of how gases interact with moving bodies. The two main classified forces acting in an airfoil are pressure and shear stress. These exist because of various principles, but mainly the pressure occurs because of the continuity equation where one might expect to obtain lower pressure on the upper part of the airfoil, while a higher pressure on the bottom to generate Lift. The shear stress is generated by viscous effects and the boundary layer.

EXPERIMENTAL DATA

CONCLUSION Having achieved the objective of the experiment, here are a few things that might summarize and conclude the experiment: Pressure Coefficient distribution is strongly related with Angle of Attack and how this angle generates Lift in the airfoil Pressure Distribution along the airfoil’s upper and lower surface are dependent with the same angle of attack, not with velocity. Velocity only changes the magnitude of this pressure distribution. Lift is generated at a certain range of angle of attacks, and if you step out of this range and get to the critical angle of attack, the airfoil will stall and will be rendered useless to generate lift in the aircraft.

RECOMENDATIONS Use wind tunnel in a large area. Keep air inlet and outlet clear. Use a servo motor with high precision to control the angle of attack of the wing. Make sure that all lines don’t have air in them for better precision. Make sure wing is well fixed to prevent vibration at higher angle of attack. Use a program that averages the measurements for easier interpretation of data during the experiment.

QUESTIONS?