Apparatus and Procedure ref

Apparatus and Procedure ref - Flow Over a NACA 0012 Airfoil...

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Flow Over a NACA 0012 Airfoil Lab 1 Tawnee Buckingham University of Texas at Austin Department of Aerospace Engineering and Engineering Mechanics Dr. D. Goldstein March 3, 2006
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Apparatus and Procedure The flow over a NACA 0012 airfoil was examined in the wind tunnel at the University of Texas at Austin W.R. Woolrich Laboratories. The tunnel has a Westinghouse 75hp motor (model AADP), and the wake measurements were recorded through a National Instruments PCI-6023E. The set-up of the lab can be seen in Figure 1. The main purpose of the lab was to utilize various techniques for flow visualization and the measuring of wake profiles. Flow visualization was achieved using a smoke wire, a smoke wand, and tufts. Wake profile measurements were taken using a hotwire and pitot probe. Barometric pressure and temperature measurements were recorded at the beginning of the lab. I. Flow Visualization a) Smoke Wire The smoke wire was located at the opening of the nozzle of the wind tunnel and was coated in oil that was heated up by the wire and vaporized, producing smoke. The smoke allowed the flow over the airfoil to be examined, helping to identify features such as separation and vortices. This technique was used at low wind speeds/low Reynolds numbers (<30 ft/s or 9.144 m/s) because at higher Reynolds numbers the oil will be blown off the wire before it can vaporize and thus be useless. Visualization was examined at low Reynolds number ( 10ft/s=3.05m/s), at angles of attack from 0° to 15° in increments of 5°. Separation, vortices, reverse flow, and stall were observed. Sketches were drawn showing the flow and any changes with increased angle of attack. b) Smoke Wand The smoke wand was a hand held tube that produced smoke by burning oil collected at its tip. This method allowed flow visualization at higher Reynolds numbers and at various locations in the airfoil. The higher Reynolds numbers along with the smoke wand allow the air flow to follow the airfoil more closely.
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Observations were made at Reynolds numbers 1.96e5 and 3.10e5, at angles of attack from 0° to 15° in increments of 5°. Separation, attachment, vortices, reverse
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Apparatus and Procedure ref - Flow Over a NACA 0012 Airfoil...

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