Abstract - calculate the pressure coefficient. It was...

Info iconThis preview shows page 1. Sign up to view the full content.

View Full Document Right Arrow Icon
1 ABSTRACT Both qualitative and quantitative measurements were taken on a symmetric airfoil, the NACA 0012, in a closed circuit wind tunnel to fundamentally understand the basics of streamlined bodies in a flow. Qualitatively a smoke wire was used to visualize the flow and then tufts atop the airfoil were used to fine the angle of attack of separation and reattachment at three different Reynolds numbers, 170,000, 235,000, and 300,000. Quantitative pressure measurements were taken to calculate the wake velocity profile and then the coefficient of drag at a Reynolds number of 143,000 and an angle of attack of zero degrees. Also in the same flow and angle of attack the pressure at the surface of the airfoil was found via pressure ports to
Background image of page 1
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: calculate the pressure coefficient. It was witnessed that the angle of attack with which flow separation occurred at increased as the Reynolds number increased. Also once the flow was separated, in order for it to reattach, it required at lower angle of attack at which it separated. The drag coefficient calculated to be 0.012. When comparing the distribution of the pressure coefficient on the top of the airfoil to the bottom, they turned out to be very similar, which is what is expected for at symmetric airfoil at a zero degree angle of attack. For further studies it would be useful to complete the same procedures just at different Reynolds numbers and angles of attack to ultimately know how the NACA 0012 will behave in any flow....
View Full Document

Ask a homework question - tutors are online