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Low Reynolds number response of a symmetric airfoil to viscous vortical gusts

<p>The response of a NACA0012 airfoil impacted by viscous vortical gusts at low Reynolds numbers is investigated performing Direct Numerical Simulations of the two-dimensional incompressible flow. This database contains the time history of the aerodynamic force coefficients of the airfoil during the interaction with the vortical gust. The airfoil, set at a fixed angle of attack alpha, is impacted by Taylor/Lamb-Oseen vortical gust, which are characterized by a diameter <em>D</em>, a intensity <em>v_0m</em>, and a vertical separation <em>h</em>. Direct Numerical Simulations are run for a range of values for the angle of attack, the size and intensity of the vortical gust, and the vertical separations. All simulations are run at a fixed Reynolds number Re=1000, based on the airfoil chord <em>c</em> and the free-stream velocity <em>U_&infin;</em>.</p> <p>More details on the database and the corresponding simulations can be found in&nbsp;Mart&iacute;nez-Muriel &amp; Flores (2020),&nbsp;Analysis of vortical gust impact on airfoils at low Reynolds number, J. Fluids and Struct, 99.&nbsp;</p> <p><strong>Contents</strong><br> The database consist on a single ASCII file for each case. After a short, self-explanatory header, each file has 7 columns with the following data:&nbsp;</p> <ul> <li>time,&nbsp;<em>t U_&infin;/c</em></li> <li>cl: lift coefficient,&nbsp;<em>c_l</em></li> <li>cd: drag coefficient,&nbsp;<em>c_d</em></li> <li>cm: coefficient of moments with respect to c/4,&nbsp;<em>c_m</em></li> <li>dcl: &nbsp;perturbation of <em>c_l</em> with respect to steady state value,&nbsp;∆<em>c_l</em>&nbsp;</li> <li>dcd: &nbsp;perturbation of <em>c_d</em> with respect to steady state value,&nbsp;∆<em>c_d</em>&nbsp;</li> <li>dcm: &nbsp;perturbation of <em>c_m</em> with respect to steady state value,&nbsp;∆<em>c_m</em>&nbsp;</li> </ul> <p>Reference time (t=0) is taken as the time at which the center of the vortical gust reaches the position of the leading edge of the airfoil (if advected at a velocity <em>U_&infin;</em>).&nbsp;<br> <br> <strong>Nomenclature&nbsp;</strong><br> The names of the files will follow the acronym t_AaYyDdVv.txt, where the lowecase letters are placeholders for:&nbsp;</p> <table> <tbody> <tr> <td>&nbsp;t&nbsp;</td> <td>&nbsp;Type of vortical gust</td> <td>&nbsp;T: Taylor, LO: Lamb-Oseen</td> </tr> <tr> <td>&nbsp;a&nbsp;</td> <td>&nbsp;Angle of attack&nbsp;</td> <td><em>&nbsp;&alpha;</em> = [+8,0,-8] deg</td> </tr> <tr> <td>&nbsp;y&nbsp;</td> <td>&nbsp;Initial vertical position of the centre of the vortex</td> <td><em>&nbsp;h/c&nbsp;</em>= [0,0.5,1]</td> </tr> <tr> <td>&nbsp;d&nbsp;</td> <td>&nbsp;Diameter of the core of the vortex&nbsp;</td> <td><em>&nbsp;D/c&nbsp;</em>= [0.5,1,2]</td> </tr> <tr> <td>&nbsp;v&nbsp;</td> <td>&nbsp;Circumferential velocity&nbsp;</td> <td><em>&nbsp;v_0m</em>/<em>U_&infin;</em>&nbsp;= [0.1,0.3,1]</td> </tr> </tbody> </table>