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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.7174 0.02771 0.02309 -0.0390 0.9961 0.0163 -8.750 -0.6949 0.02500 0.01998 -0.0396 0.9900 0.0164 -8.500 -0.6679 0.02342 0.01824 -0.0403 0.9849 0.0166 -8.250 -0.6399 0.02232 0.01703 -0.0409 0.9801 0.0168 -8.000 -0.6117 0.02137 0.01597 -0.0413 0.9752 0.0169 -7.750 -0.5847 0.02051 0.01501 -0.0414 0.9696 0.0171 -7.500 -0.5591 0.01973 0.01411 -0.0411 0.9630 0.0173 -7.250 -0.5348 0.01894 0.01322 -0.0404 0.9547 0.0175 -7.000 -0.5104 0.01819 0.01235 -0.0396 0.9466 0.0177 -6.750 -0.4862 0.01747 0.01152 -0.0388 0.9383 0.0180 -6.500 -0.4617 0.01678 0.01072 -0.0380 0.9299 0.0183 -6.250 -0.4376 0.01613 0.00996 -0.0369 0.9208 0.0186 -6.000 -0.4137 0.01554 0.00925 -0.0358 0.9069 0.0189 -5.750 -0.3899 0.01501 0.00859 -0.0346 0.8895 0.0192 -5.500 -0.3648 0.01455 0.00801 -0.0336 0.8729 0.0194 -5.250 -0.3390 0.01400 0.00741 -0.0330 0.8616 0.0198 -5.000 -0.3125 0.01361 0.00699 -0.0325 0.8505 0.0201 -4.750 -0.2854 0.01325 0.00660 -0.0321 0.8388 0.0205 -4.500 -0.2584 0.01293 0.00621 -0.0316 0.8268 0.0210 -4.250 -0.2310 0.01261 0.00585 -0.0313 0.8144 0.0216 -4.000 -0.2034 0.01233 0.00550 -0.0309 0.8011 0.0223 -3.750 -0.1759 0.01204 0.00513 -0.0305 0.7863 0.0229 -3.500 -0.1485 0.01173 0.00479 -0.0302 0.7710 0.0235 -3.250 -0.1208 0.01150 0.00451 -0.0299 0.7534 0.0242 -3.000 -0.0932 0.01131 0.00423 -0.0295 0.7263 0.0249 -2.750 -0.0658 0.01119 0.00395 -0.0291 0.6896 0.0258 -2.500 -0.0384 0.01111 0.00369 -0.0287 0.6464 0.0266 -2.250 -0.0109 0.01106 0.00349 -0.0285 0.6028 0.0277 -2.000 0.0169 0.01107 0.00333 -0.0283 0.5604 0.0291 -1.750 0.0448 0.01108 0.00318 -0.0281 0.5185 0.0306 -1.500 0.0727 0.01111 0.00306 -0.0280 0.4773 0.0322 -1.250 0.1008 0.01116 0.00295 -0.0279 0.4407 0.0342 -1.000 0.1289 0.01119 0.00287 -0.0279 0.4091 0.0373 -0.750 0.1572 0.01121 0.00281 -0.0278 0.3828 0.0422 -0.500 0.1855 0.01123 0.00276 -0.0278 0.3594 0.0501 -0.250 0.2139 0.01123 0.00272 -0.0278 0.3377 0.0626 0.000 0.2423 0.01122 0.00271 -0.0278 0.3188 0.0825 0.250 0.2706 0.01120 0.00271 -0.0278 0.3013 0.1129 0.500 0.2988 0.01114 0.00271 -0.0278 0.2847 0.1575 0.750 0.3245 0.01002 0.00265 -0.0282 0.2684 0.5180 1.000 0.3495 0.00949 0.00275 -0.0276 0.2519 0.7240 1.250 0.3734 0.00939 0.00289 -0.0264 0.2359 0.8206 1.750 0.4205 0.00961 0.00314 -0.0236 0.2042 0.9023 2.000 0.4427 0.00977 0.00326 -0.0219 0.1912 0.9293 2.250 0.4654 0.00993 0.00336 -0.0203 0.1809 0.9527 2.500 0.4919 0.01010 0.00344 -0.0197 0.1716 0.9681 2.750 0.5227 0.01024 0.00352 -0.0202 0.1646 0.9757 3.000 0.5548 0.01045 0.00363 -0.0210 0.1574 0.9808 3.250 0.5877 0.01061 0.00374 -0.0220 0.1519 0.9856 3.500 0.6208 0.01082 0.00387 -0.0230 0.1456 0.9905 3.750 0.6537 0.01103 0.00402 -0.0241 0.1403 0.9953 4.000 0.6859 0.01121 0.00415 -0.0250 0.1356 1.0000 4.250 0.7112 0.01142 0.00430 -0.0245 0.1315 1.0000 4.500 0.7373 0.01164 0.00447 -0.0241 0.1279 1.0000 4.750 0.7641 0.01183 0.00463 -0.0239 0.1249 1.0000 5.000 0.7910 0.01205 0.00481 -0.0237 0.1216 1.0000 5.250 0.8178 0.01230 0.00502 -0.0235 0.1183 1.0000 5.500 0.8447 0.01255 0.00523 -0.0234 0.1154 1.0000 5.750 0.8719 0.01277 0.00543 -0.0233 0.1129 1.0000 6.000 0.8988 0.01302 0.00566 -0.0231 0.1103 1.0000 6.250 0.9256 0.01329 0.00590 -0.0230 0.1080 1.0000 6.500 0.9520 0.01360 0.00617 -0.0228 0.1056 1.0000 6.750 0.9787 0.01387 0.00644 -0.0226 0.1041 1.0000 7.000 1.0053 0.01413 0.00671 -0.0224 0.1025 1.0000 7.250 1.0317 0.01442 0.00699 -0.0223 0.1009 1.0000 7.500 1.0578 0.01472 0.00729 -0.0220 0.0993 1.0000 7.750 1.0836 0.01504 0.00760 -0.0218 0.0977 1.0000 8.000 1.1090 0.01540 0.00794 -0.0215 0.0962 1.0000 8.250 1.1339 0.01581 0.00833 -0.0212 0.0946 1.0000 8.500 1.1595 0.01611 0.00866 -0.0209 0.0936 1.0000 8.750 1.1847 0.01643 0.00901 -0.0206 0.0925 1.0000 9.000 1.2096 0.01678 0.00939 -0.0202 0.0914 1.0000 9.250 1.2340 0.01715 0.00978 -0.0199 0.0904 1.0000 9.500 1.2581 0.01754 0.01018 -0.0194 0.0893 1.0000 9.750 1.2817 0.01796 0.01061 -0.0189 0.0884 1.0000 10.000 1.3048 0.01840 0.01106 -0.0184 0.0874 1.0000 10.250 1.3270 0.01889 0.01156 -0.0178 0.0865 1.0000 10.500 1.3481 0.01945 0.01214 -0.0170 0.0855 1.0000 10.750 1.3696 0.01994 0.01267 -0.0163 0.0849 1.0000 11.000 1.3912 0.02041 0.01319 -0.0156 0.0844 1.0000 11.250 1.4121 0.02090 0.01374 -0.0148 0.0838 1.0000 11.500 1.4322 0.02141 0.01431 -0.0139 0.0832 1.0000 11.750 1.4513 0.02195 0.01490 -0.0129 0.0826 1.0000 12.000 1.4685 0.02251 0.01551 -0.0116 0.0819 1.0000 12.250 1.4844 0.02310 0.01616 -0.0102 0.0813 1.0000 12.500 1.4998 0.02374 0.01685 -0.0088 0.0806 1.0000 12.750 1.5146 0.02445 0.01762 -0.0075 0.0800 1.0000 13.000 1.5286 0.02524 0.01845 -0.0062 0.0795 1.0000 13.250 1.5418 0.02611 0.01937 -0.0049 0.0790 1.0000 13.500 1.5541 0.02707 0.02039 -0.0037 0.0785 1.0000 13.750 1.5652 0.02815 0.02153 -0.0025 0.0780 1.0000 14.000 1.5752 0.02937 0.02280 -0.0014 0.0775 1.0000 14.250 1.5836 0.03076 0.02424 -0.0003 0.0770 1.0000 14.500 1.5916 0.03224 0.02580 0.0006 0.0765 1.0000 14.750 1.6015 0.03361 0.02726 0.0013 0.0763 1.0000 15.000 1.6106 0.03511 0.02886 0.0019 0.0760 1.0000 15.250 1.6187 0.03674 0.03059 0.0024 0.0757 1.0000 15.500 1.6257 0.03853 0.03248 0.0027 0.0754 1.0000 15.750 1.6317 0.04047 0.03453 0.0029 0.0751 1.0000 16.000 1.6366 0.04260 0.03676 0.0030 0.0748 1.0000 16.250 1.6402 0.04491 0.03918 0.0029 0.0745 1.0000 16.500 1.6428 0.04743 0.04180 0.0026 0.0742 1.0000 16.750 1.6441 0.05015 0.04463 0.0022 0.0738 1.0000 17.000 1.6439 0.05310 0.04769 0.0016 0.0735 1.0000 17.250 1.6426 0.05628 0.05098 0.0007 0.0732 1.0000 17.500 1.6404 0.05969 0.05450 -0.0003 0.0728 1.0000 17.750 1.6367 0.06337 0.05829 -0.0016 0.0725 1.0000 18.000 1.6318 0.06732 0.06235 -0.0031 0.0721 1.0000 18.250 1.6257 0.07151 0.06666 -0.0048 0.0718 1.0000 18.500 1.6180 0.07599 0.07124 -0.0066 0.0715 1.0000 18.750 1.6089 0.08072 0.07609 -0.0087 0.0712 1.0000 19.000 1.5988 0.08566 0.08114 -0.0109 0.0709 1.0000 19.250 1.5881 0.09077 0.08635 -0.0132 0.0706 1.0000