XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1012R8 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.4349 0.07912 0.07410 -0.0292 1.0000 0.0451 -7.750 -0.4304 0.07612 0.07111 -0.0294 1.0000 0.0435 -7.250 -0.4541 0.06354 0.05824 -0.0341 1.0000 0.0391 -7.000 -0.4537 0.06059 0.05524 -0.0330 1.0000 0.0388 -6.750 -0.4544 0.05758 0.05215 -0.0315 1.0000 0.0385 -6.500 -0.4549 0.05452 0.04896 -0.0296 1.0000 0.0381 -6.250 -0.4545 0.05137 0.04565 -0.0276 1.0000 0.0380 -6.000 -0.4524 0.04812 0.04217 -0.0255 1.0000 0.0382 -5.750 -0.4483 0.04473 0.03846 -0.0235 1.0000 0.0386 -5.500 -0.4202 0.04001 0.03317 -0.0258 0.9939 0.0391 -5.250 -0.3899 0.03639 0.02906 -0.0277 0.9874 0.0391 -5.000 -0.3566 0.03315 0.02530 -0.0296 0.9818 0.0393 -4.750 -0.3218 0.03090 0.02278 -0.0315 0.9755 0.0397 -4.500 -0.2845 0.02913 0.02082 -0.0337 0.9693 0.0403 -4.250 -0.2432 0.02746 0.01893 -0.0364 0.9625 0.0415 -4.000 -0.2048 0.02590 0.01706 -0.0382 0.9517 0.0436 -3.750 -0.1684 0.02443 0.01534 -0.0393 0.9398 0.0452 -3.500 -0.1348 0.02333 0.01420 -0.0401 0.9280 0.0465 -3.250 -0.1015 0.02228 0.01308 -0.0407 0.9175 0.0479 -3.000 -0.0704 0.02134 0.01202 -0.0407 0.9059 0.0501 -2.750 -0.0417 0.02062 0.01134 -0.0404 0.8926 0.0527 -2.500 -0.0127 0.01992 0.01064 -0.0401 0.8795 0.0558 -2.250 0.0160 0.01916 0.00987 -0.0395 0.8664 0.0584 -2.000 0.0424 0.01857 0.00935 -0.0387 0.8504 0.0620 -1.750 0.0683 0.01804 0.00883 -0.0377 0.8333 0.0673 -1.500 0.0943 0.01755 0.00833 -0.0366 0.8148 0.0737 -1.250 0.1199 0.01706 0.00784 -0.0355 0.7933 0.0828 -1.000 0.1448 0.01660 0.00739 -0.0341 0.7654 0.0983 -0.750 0.1697 0.01611 0.00694 -0.0328 0.7336 0.1285 -0.500 0.1931 0.01526 0.00651 -0.0316 0.6985 0.2450 -0.250 0.2000 0.01350 0.00680 -0.0256 0.6670 0.8076 0.000 0.2271 0.01364 0.00684 -0.0230 0.6269 0.9092 0.250 0.2709 0.01391 0.00675 -0.0246 0.5768 0.9654 0.500 0.3515 0.01426 0.00652 -0.0343 0.5088 1.0000 0.750 0.3730 0.01448 0.00642 -0.0332 0.4723 1.0000 1.000 0.3945 0.01471 0.00636 -0.0320 0.4395 1.0000 1.250 0.4161 0.01495 0.00635 -0.0309 0.4111 1.0000 1.500 0.4376 0.01522 0.00638 -0.0298 0.3852 1.0000 1.750 0.4590 0.01551 0.00643 -0.0286 0.3619 1.0000 2.000 0.4808 0.01578 0.00652 -0.0275 0.3404 1.0000 2.250 0.5027 0.01608 0.00663 -0.0264 0.3199 1.0000 2.500 0.5246 0.01639 0.00677 -0.0254 0.3005 1.0000 2.750 0.5469 0.01673 0.00694 -0.0244 0.2825 1.0000 3.000 0.5696 0.01707 0.00713 -0.0234 0.2656 1.0000 3.250 0.5926 0.01744 0.00734 -0.0226 0.2501 1.0000 3.750 0.6396 0.01822 0.00785 -0.0211 0.2239 1.0000 4.000 0.6634 0.01864 0.00816 -0.0204 0.2134 1.0000 4.250 0.6870 0.01911 0.00847 -0.0197 0.2044 1.0000 4.500 0.7113 0.01955 0.00885 -0.0192 0.1962 1.0000 4.750 0.7350 0.02005 0.00924 -0.0185 0.1893 1.0000 5.000 0.7591 0.02055 0.00968 -0.0180 0.1829 1.0000 5.250 0.7833 0.02105 0.01013 -0.0174 0.1768 1.0000 5.500 0.8065 0.02166 0.01060 -0.0168 0.1718 1.0000 5.750 0.8310 0.02219 0.01114 -0.0163 0.1669 1.0000 6.000 0.8550 0.02275 0.01169 -0.0158 0.1626 1.0000 6.250 0.8786 0.02337 0.01224 -0.0152 0.1588 1.0000 6.500 0.9020 0.02406 0.01285 -0.0147 0.1554 1.0000 6.750 0.9261 0.02467 0.01353 -0.0142 0.1516 1.0000 7.000 0.9496 0.02531 0.01419 -0.0137 0.1481 1.0000 7.250 0.9728 0.02597 0.01481 -0.0131 0.1451 1.0000 7.500 0.9958 0.02674 0.01549 -0.0126 0.1427 1.0000 7.750 1.0190 0.02754 0.01635 -0.0121 0.1403 1.0000 8.000 1.0419 0.02833 0.01726 -0.0116 0.1378 1.0000 8.250 1.0644 0.02914 0.01813 -0.0110 0.1354 1.0000 8.500 1.0865 0.02994 0.01895 -0.0104 0.1332 1.0000 8.750 1.1084 0.03074 0.01976 -0.0099 0.1312 1.0000 9.000 1.1304 0.03162 0.02058 -0.0094 0.1294 1.0000 9.250 1.1511 0.03265 0.02169 -0.0087 0.1277 1.0000 9.500 1.1706 0.03373 0.02296 -0.0079 0.1259 1.0000 9.750 1.1896 0.03486 0.02425 -0.0072 0.1243 1.0000 10.000 1.2080 0.03602 0.02553 -0.0063 0.1228 1.0000 10.250 1.2258 0.03719 0.02681 -0.0055 0.1214 1.0000 10.500 1.2431 0.03835 0.02806 -0.0046 0.1201 1.0000 10.750 1.2604 0.03948 0.02925 -0.0038 0.1189 1.0000 11.000 1.2782 0.04061 0.03039 -0.0031 0.1178 1.0000 11.250 1.2964 0.04184 0.03162 -0.0024 0.1167 1.0000 11.500 1.3056 0.04352 0.03352 -0.0010 0.1156 1.0000 11.750 1.3090 0.04544 0.03572 0.0009 0.1146 1.0000 12.000 1.3077 0.04746 0.03799 0.0031 0.1136 1.0000 12.250 1.3038 0.04976 0.04053 0.0052 0.1127 1.0000 12.500 1.2968 0.05241 0.04343 0.0069 0.1120 1.0000 12.750 1.2859 0.05555 0.04681 0.0080 0.1113 1.0000 13.000 1.2695 0.05944 0.05095 0.0085 0.1107 1.0000 13.250 1.2435 0.06473 0.05653 0.0077 0.1101 1.0000 13.500 1.1833 0.07529 0.06749 0.0028 0.1097 1.0000