XFOIL Version 6.94 Calculated polar for: S4083 (8%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4315 0.00748 0.00210 -0.0891 0.6388 1.0000 0.500 0.4809 0.00791 0.00211 -0.0874 0.5921 1.0000 1.000 0.5316 0.00830 0.00219 -0.0861 0.5559 1.0000 1.500 0.5830 0.00868 0.00232 -0.0849 0.5261 1.0000 2.000 0.6345 0.00908 0.00250 -0.0838 0.5006 1.0000 2.500 0.6865 0.00943 0.00274 -0.0828 0.4765 1.0000 3.000 0.7383 0.00981 0.00300 -0.0818 0.4554 1.0000 3.500 0.7901 0.01023 0.00334 -0.0808 0.4359 1.0000 4.000 0.8419 0.01062 0.00370 -0.0798 0.4165 1.0000 4.500 0.8933 0.01099 0.00408 -0.0788 0.3965 1.0000 5.000 0.9444 0.01140 0.00454 -0.0777 0.3769 1.0000 5.500 0.9948 0.01184 0.00500 -0.0765 0.3565 1.0000 6.000 1.0447 0.01229 0.00554 -0.0753 0.3347 1.0000 6.500 1.0934 0.01273 0.00604 -0.0738 0.3068 1.0000 7.000 1.1410 0.01322 0.00656 -0.0723 0.2672 1.0000 7.500 1.1858 0.01406 0.00732 -0.0704 0.2139 1.0000 8.000 1.2269 0.01538 0.00842 -0.0682 0.1520 1.0000 8.500 1.2563 0.01795 0.01038 -0.0645 0.0544 1.0000 9.000 1.2791 0.02111 0.01346 -0.0593 0.0157 1.0000 9.500 1.3048 0.02353 0.01617 -0.0548 0.0128 1.0000 10.000 1.3104 0.02700 0.01997 -0.0476 0.0116 1.0000 10.500 1.3064 0.03058 0.02381 -0.0396 0.0112 1.0000 11.000 1.3070 0.03434 0.02786 -0.0338 0.0110 1.0000 11.500 1.3060 0.03902 0.03285 -0.0295 0.0110 1.0000 12.000 1.3038 0.04470 0.03887 -0.0268 0.0110 1.0000 12.500 1.2972 0.05157 0.04614 -0.0255 0.0110 1.0000 13.000 1.2833 0.06002 0.05500 -0.0259 0.0111 1.0000 13.500 1.2588 0.07084 0.06628 -0.0283 0.0113 1.0000 14.000 1.2419 0.08048 0.07626 -0.0325 0.0114 1.0000 14.500 1.2243 0.09090 0.08699 -0.0379 0.0116 1.0000 15.000 1.2015 0.10326 0.09966 -0.0450 0.0118 1.0000 15.500 1.1751 0.11772 0.11444 -0.0539 0.0121 1.0000 16.000 1.1415 0.13565 0.13270 -0.0654 0.0124 1.0000 16.500 1.0933 0.16051 0.15786 -0.0811 0.0129 1.0000 17.000 1.0240 0.20085 0.19817 -0.1015 0.0168 1.0000