A copy of this work was available on the public web and has been preserved in the Wayback Machine. The capture dates from 2020; you can also visit the original URL.
The file type is
Experimental Investigation of the Flow Field around NACA0012 Airfoil
In this study, an experimental investigation of the flow field around NACA0012 airfoil was carried out in a wind tunnel under the effects of the Reynolds number and angle of attack. The Reynolds number based on the chord length of airfoil and the attack angle was varied from 9.7x104 to 1.9x105 and 0 to 140 respectively. Mean velocities were measured by a constant temperature anemometer and static pressures by a micro-manometer. The results showed that the pressure and lift coefficientsdoi:10.5281/zenodo.3348421 fatcat:5s3hfrspzjb53kbpyxvjscicva