XFOIL Version 6.94 Calculated polar for: SOKOLOV AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.5256 0.01004 0.00276 -0.1269 0.6362 0.0747 0.500 0.5836 0.01004 0.00280 -0.1269 0.6121 0.1150 1.000 0.6416 0.01009 0.00279 -0.1269 0.5965 0.1317 2.000 0.7575 0.01001 0.00291 -0.1272 0.5613 0.2032 2.500 0.8154 0.00986 0.00323 -0.1276 0.5478 0.3889 3.000 0.8727 0.00979 0.00348 -0.1277 0.5324 0.5185 3.500 0.9231 0.00903 0.00363 -0.1260 0.5166 1.0000 4.000 0.9799 0.00930 0.00382 -0.1258 0.4971 1.0000 4.500 1.0363 0.00961 0.00407 -0.1255 0.4728 1.0000 5.000 1.0916 0.00997 0.00431 -0.1252 0.4393 1.0000 5.500 1.1439 0.01074 0.00473 -0.1243 0.3594 1.0000 6.000 1.1947 0.01168 0.00539 -0.1235 0.3104 1.0000 6.500 1.2471 0.01237 0.00602 -0.1228 0.2878 1.0000 7.000 1.2978 0.01320 0.00674 -0.1219 0.2516 1.0000 7.500 1.3430 0.01465 0.00772 -0.1203 0.1626 1.0000 8.000 1.3863 0.01615 0.00906 -0.1184 0.1352 1.0000 8.500 1.4319 0.01725 0.01013 -0.1167 0.1133 1.0000 9.000 1.4671 0.01928 0.01174 -0.1137 0.0504 1.0000 9.500 1.5004 0.02121 0.01365 -0.1102 0.0371 1.0000 10.000 1.5305 0.02308 0.01557 -0.1063 0.0318 1.0000 10.500 1.5512 0.02513 0.01773 -0.1010 0.0286 1.0000 11.000 1.5587 0.02786 0.02058 -0.0944 0.0266 1.0000 11.500 1.5722 0.03066 0.02356 -0.0897 0.0246 1.0000 12.000 1.5748 0.03481 0.02783 -0.0854 0.0233 1.0000 12.500 1.5867 0.03865 0.03190 -0.0828 0.0216 1.0000 13.000 1.5892 0.04376 0.03715 -0.0805 0.0207 1.0000 13.500 1.5861 0.04969 0.04326 -0.0786 0.0197 1.0000 14.000 1.5934 0.05482 0.04860 -0.0780 0.0180 1.0000 14.500 1.5831 0.06200 0.05591 -0.0770 0.0169 1.0000 15.000 1.5781 0.06842 0.06246 -0.0754 0.0170 1.0000 15.500 1.5799 0.07543 0.06981 -0.0773 0.0159 1.0000 16.000 1.5774 0.08266 0.07727 -0.0785 0.0154 1.0000 17.000 1.5583 0.09883 0.09387 -0.0799 0.0149 1.0000 18.000 1.5250 0.11997 0.11551 -0.0873 0.0126 1.0000 18.500 1.5081 0.13296 0.12867 -0.0957 0.0099 1.0000 19.000 1.5122 0.13879 0.13455 -0.0968 0.0115 1.0000