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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4452 0.08601 0.08234 -0.0193 1.0000 0.0301 -8.500 -0.4430 0.08229 0.07867 -0.0216 1.0000 0.0306 -8.000 -0.4824 0.06446 0.06066 -0.0352 1.0000 0.0262 -7.750 -0.4816 0.06101 0.05716 -0.0357 1.0000 0.0260 -7.500 -0.4830 0.05750 0.05358 -0.0353 1.0000 0.0259 -7.250 -0.4877 0.05415 0.05012 -0.0335 1.0000 0.0257 -7.000 -0.4867 0.05003 0.04583 -0.0328 0.9978 0.0254 -6.750 -0.4682 0.04373 0.03914 -0.0358 0.9912 0.0252 -6.500 -0.4482 0.03691 0.03176 -0.0380 0.9851 0.0251 -6.250 -0.4262 0.03112 0.02529 -0.0392 0.9790 0.0252 -6.000 -0.3985 0.02716 0.02071 -0.0403 0.9740 0.0256 -5.750 -0.3700 0.02429 0.01722 -0.0408 0.9678 0.0263 -5.500 -0.3374 0.02329 0.01618 -0.0420 0.9623 0.0269 -5.250 -0.3086 0.02251 0.01535 -0.0423 0.9523 0.0276 -5.000 -0.2800 0.02148 0.01416 -0.0422 0.9393 0.0284 -4.750 -0.2531 0.02030 0.01276 -0.0415 0.9246 0.0291 -4.500 -0.2270 0.01922 0.01148 -0.0406 0.9110 0.0297 -4.250 -0.2005 0.01830 0.01039 -0.0399 0.9005 0.0303 -4.000 -0.1746 0.01763 0.00972 -0.0392 0.8892 0.0309 -3.750 -0.1487 0.01704 0.00912 -0.0384 0.8774 0.0317 -3.500 -0.1228 0.01650 0.00853 -0.0375 0.8659 0.0328 -3.250 -0.0968 0.01600 0.00792 -0.0367 0.8526 0.0344 -3.000 -0.0709 0.01552 0.00748 -0.0360 0.8390 0.0357 -2.750 -0.0450 0.01509 0.00702 -0.0351 0.8245 0.0371 -2.500 -0.0190 0.01465 0.00653 -0.0343 0.8090 0.0386 -2.250 0.0070 0.01425 0.00609 -0.0335 0.7911 0.0401 -2.000 0.0330 0.01396 0.00576 -0.0327 0.7660 0.0427 -1.750 0.0586 0.01369 0.00537 -0.0317 0.7338 0.0456 -1.500 0.0844 0.01348 0.00503 -0.0308 0.6967 0.0489 -1.250 0.1107 0.01329 0.00471 -0.0301 0.6600 0.0531 -1.000 0.1371 0.01317 0.00446 -0.0295 0.6211 0.0607 -0.750 0.1634 0.01310 0.00424 -0.0289 0.5780 0.0729 -0.500 0.1897 0.01306 0.00409 -0.0284 0.5353 0.0939 -0.250 0.2159 0.01301 0.00399 -0.0280 0.4940 0.1347 0.000 0.2410 0.01255 0.00387 -0.0279 0.4576 0.2758 0.250 0.2545 0.01108 0.00406 -0.0249 0.4305 0.7565 0.500 0.2725 0.01115 0.00426 -0.0216 0.4038 0.8585 0.750 0.2950 0.01137 0.00438 -0.0196 0.3797 0.9089 1.000 0.3225 0.01159 0.00446 -0.0188 0.3562 0.9418 1.250 0.3576 0.01184 0.00453 -0.0198 0.3321 0.9694 1.500 0.4093 0.01216 0.00461 -0.0245 0.3061 0.9870 1.750 0.4521 0.01241 0.00467 -0.0276 0.2832 0.9949 2.000 0.4881 0.01263 0.00473 -0.0293 0.2626 0.9997 2.250 0.5109 0.01283 0.00479 -0.0285 0.2457 1.0000 2.500 0.5331 0.01305 0.00487 -0.0274 0.2301 1.0000 2.750 0.5554 0.01329 0.00497 -0.0264 0.2162 1.0000 3.000 0.5778 0.01355 0.00510 -0.0254 0.2041 1.0000 3.250 0.6009 0.01380 0.00525 -0.0245 0.1937 1.0000 3.500 0.6243 0.01410 0.00543 -0.0237 0.1848 1.0000 3.750 0.6485 0.01438 0.00562 -0.0231 0.1766 1.0000 4.000 0.6730 0.01471 0.00585 -0.0225 0.1700 1.0000 4.250 0.6981 0.01499 0.00609 -0.0220 0.1640 1.0000 4.500 0.7231 0.01534 0.00635 -0.0215 0.1587 1.0000 4.750 0.7483 0.01568 0.00664 -0.0211 0.1541 1.0000 5.000 0.7739 0.01599 0.00693 -0.0207 0.1494 1.0000 5.250 0.7990 0.01636 0.00724 -0.0203 0.1450 1.0000 5.500 0.8239 0.01678 0.00758 -0.0198 0.1412 1.0000 5.750 0.8495 0.01711 0.00792 -0.0195 0.1377 1.0000 6.000 0.8748 0.01748 0.00828 -0.0191 0.1344 1.0000 6.250 0.8995 0.01790 0.00865 -0.0187 0.1314 1.0000 6.500 0.9234 0.01842 0.00909 -0.0182 0.1288 1.0000 6.750 0.9486 0.01880 0.00951 -0.0178 0.1264 1.0000 7.000 0.9734 0.01922 0.00995 -0.0174 0.1238 1.0000 7.250 0.9978 0.01965 0.01038 -0.0170 0.1214 1.0000 7.500 1.0216 0.02012 0.01083 -0.0165 0.1191 1.0000 7.750 1.0446 0.02069 0.01135 -0.0159 0.1171 1.0000 8.000 1.0680 0.02122 0.01190 -0.0154 0.1154 1.0000 8.250 1.0916 0.02173 0.01246 -0.0149 0.1138 1.0000 8.500 1.1147 0.02226 0.01304 -0.0143 0.1121 1.0000 8.750 1.1374 0.02282 0.01362 -0.0137 0.1106 1.0000 9.000 1.1597 0.02339 0.01421 -0.0131 0.1091 1.0000 9.250 1.1815 0.02398 0.01483 -0.0124 0.1078 1.0000 9.500 1.2024 0.02464 0.01548 -0.0117 0.1066 1.0000 9.750 1.2226 0.02541 0.01622 -0.0109 0.1053 1.0000 10.000 1.2433 0.02608 0.01697 -0.0102 0.1042 1.0000 10.250 1.2635 0.02676 0.01774 -0.0094 0.1030 1.0000 10.500 1.2830 0.02747 0.01854 -0.0085 0.1018 1.0000 10.750 1.3018 0.02822 0.01936 -0.0076 0.1007 1.0000 11.000 1.3197 0.02901 0.02022 -0.0066 0.0998 1.0000 11.250 1.3365 0.02981 0.02109 -0.0055 0.0989 1.0000 11.500 1.3513 0.03063 0.02197 -0.0041 0.0980 1.0000 11.750 1.3656 0.03150 0.02290 -0.0027 0.0973 1.0000 12.000 1.3794 0.03243 0.02388 -0.0014 0.0966 1.0000 12.250 1.3927 0.03345 0.02494 -0.0002 0.0959 1.0000 12.500 1.4060 0.03455 0.02608 0.0010 0.0952 1.0000 12.750 1.4193 0.03578 0.02734 0.0020 0.0946 1.0000 13.000 1.4290 0.03707 0.02879 0.0033 0.0941 1.0000 13.250 1.4373 0.03848 0.03036 0.0045 0.0935 1.0000 13.500 1.4443 0.04003 0.03207 0.0055 0.0928 1.0000 13.750 1.4501 0.04172 0.03391 0.0065 0.0922 1.0000 14.000 1.4548 0.04355 0.03590 0.0073 0.0915 1.0000 14.250 1.4583 0.04556 0.03805 0.0079 0.0909 1.0000 14.500 1.4607 0.04776 0.04040 0.0084 0.0903 1.0000 14.750 1.4617 0.05017 0.04296 0.0086 0.0898 1.0000 15.000 1.4613 0.05283 0.04576 0.0085 0.0893 1.0000 15.250 1.4593 0.05574 0.04881 0.0083 0.0888 1.0000 15.500 1.4558 0.05895 0.05217 0.0077 0.0884 1.0000 15.750 1.4505 0.06249 0.05585 0.0067 0.0880 1.0000 16.000 1.4433 0.06641 0.05992 0.0055 0.0876 1.0000 16.250 1.4339 0.07077 0.06442 0.0038 0.0872 1.0000 16.500 1.4218 0.07568 0.06949 0.0017 0.0869 1.0000 16.750 1.4068 0.08124 0.07520 -0.0010 0.0865 1.0000 17.000 1.3879 0.08768 0.08180 -0.0043 0.0861 1.0000 17.250 1.3591 0.09607 0.09038 -0.0090 0.0857 1.0000