XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1094R8 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.8721 0.02765 0.02433 -0.0387 1.0000 0.0118 -8.750 -0.8544 0.02541 0.02186 -0.0382 1.0000 0.0119 -8.500 -0.8342 0.02366 0.01990 -0.0376 1.0000 0.0119 -8.250 -0.8128 0.02209 0.01815 -0.0370 1.0000 0.0120 -8.000 -0.7902 0.02077 0.01666 -0.0365 1.0000 0.0121 -7.750 -0.7668 0.01957 0.01530 -0.0360 1.0000 0.0122 -7.500 -0.7427 0.01849 0.01408 -0.0354 1.0000 0.0123 -7.250 -0.7182 0.01750 0.01296 -0.0349 1.0000 0.0124 -7.000 -0.6933 0.01661 0.01195 -0.0344 1.0000 0.0126 -6.750 -0.6656 0.01577 0.01099 -0.0343 0.9955 0.0127 -6.500 -0.6360 0.01498 0.01009 -0.0346 0.9894 0.0128 -6.250 -0.6060 0.01427 0.00929 -0.0349 0.9838 0.0129 -6.000 -0.5775 0.01364 0.00857 -0.0349 0.9781 0.0131 -5.750 -0.5496 0.01311 0.00795 -0.0346 0.9726 0.0132 -5.500 -0.5235 0.01267 0.00745 -0.0339 0.9654 0.0134 -5.250 -0.4977 0.01227 0.00698 -0.0331 0.9584 0.0136 -5.000 -0.4721 0.01187 0.00652 -0.0322 0.9493 0.0137 -4.750 -0.4465 0.01148 0.00608 -0.0313 0.9395 0.0138 -4.500 -0.4223 0.01101 0.00554 -0.0302 0.9249 0.0140 -4.250 -0.3985 0.01065 0.00509 -0.0288 0.9028 0.0143 -4.000 -0.3729 0.01038 0.00474 -0.0278 0.8801 0.0145 -3.750 -0.3461 0.01015 0.00445 -0.0271 0.8653 0.0148 -3.250 -0.2912 0.00971 0.00390 -0.0260 0.8372 0.0154 -3.000 -0.2635 0.00951 0.00365 -0.0255 0.8222 0.0158 -2.750 -0.2357 0.00931 0.00339 -0.0250 0.8076 0.0162 -2.500 -0.2077 0.00915 0.00316 -0.0245 0.7905 0.0166 -2.250 -0.1798 0.00902 0.00295 -0.0240 0.7687 0.0169 -2.000 -0.1521 0.00887 0.00269 -0.0236 0.7379 0.0175 -1.750 -0.1243 0.00885 0.00252 -0.0231 0.6908 0.0181 -1.500 -0.0965 0.00888 0.00237 -0.0227 0.6361 0.0188 -1.250 -0.0684 0.00894 0.00223 -0.0223 0.5825 0.0196 -1.000 -0.0403 0.00900 0.00211 -0.0220 0.5323 0.0202 -0.750 -0.0121 0.00902 0.00199 -0.0217 0.4865 0.0215 -0.500 0.0162 0.00909 0.00191 -0.0214 0.4434 0.0228 -0.250 0.0445 0.00917 0.00184 -0.0211 0.4012 0.0241 0.000 0.0728 0.00920 0.00176 -0.0208 0.3663 0.0260 0.250 0.1012 0.00925 0.00171 -0.0205 0.3362 0.0280 0.500 0.1297 0.00929 0.00167 -0.0202 0.3107 0.0315 0.750 0.1582 0.00930 0.00164 -0.0199 0.2908 0.0384 1.000 0.1867 0.00929 0.00161 -0.0196 0.2729 0.0519 1.250 0.2151 0.00928 0.00161 -0.0194 0.2528 0.0756 1.500 0.2434 0.00928 0.00162 -0.0191 0.2289 0.1136 1.750 0.2716 0.00926 0.00164 -0.0189 0.2050 0.1650 2.000 0.2989 0.00830 0.00163 -0.0192 0.1880 0.5229 2.250 0.3258 0.00781 0.00170 -0.0188 0.1750 0.7228 2.500 0.3522 0.00766 0.00180 -0.0180 0.1644 0.8180 2.750 0.3759 0.00760 0.00191 -0.0165 0.1555 0.8901 3.000 0.3964 0.00762 0.00201 -0.0141 0.1482 0.9400 3.250 0.4205 0.00773 0.00208 -0.0127 0.1398 0.9624 3.500 0.4473 0.00781 0.00212 -0.0119 0.1340 0.9737 3.750 0.4773 0.00793 0.00218 -0.0119 0.1278 0.9803 4.000 0.5086 0.00807 0.00226 -0.0121 0.1220 0.9865 4.500 0.5714 0.00835 0.00244 -0.0127 0.1125 1.0000 4.750 0.5995 0.00850 0.00255 -0.0124 0.1084 1.0000 5.000 0.6276 0.00865 0.00266 -0.0120 0.1049 1.0000 5.250 0.6557 0.00882 0.00278 -0.0117 0.1009 1.0000 5.500 0.6837 0.00901 0.00292 -0.0113 0.0971 1.0000 5.750 0.7119 0.00915 0.00305 -0.0109 0.0955 1.0000 6.000 0.7399 0.00931 0.00320 -0.0106 0.0934 1.0000 6.250 0.7679 0.00949 0.00335 -0.0102 0.0911 1.0000 6.500 0.7957 0.00969 0.00352 -0.0098 0.0887 1.0000 6.750 0.8234 0.00990 0.00370 -0.0094 0.0862 1.0000 7.000 0.8512 0.01008 0.00387 -0.0090 0.0850 1.0000 7.250 0.8790 0.01026 0.00406 -0.0086 0.0840 1.0000 7.500 0.9066 0.01045 0.00424 -0.0082 0.0826 1.0000 7.750 0.9341 0.01066 0.00444 -0.0078 0.0810 1.0000 8.000 0.9614 0.01088 0.00465 -0.0074 0.0794 1.0000 8.250 0.9886 0.01112 0.00488 -0.0069 0.0779 1.0000 8.500 1.0156 0.01137 0.00513 -0.0065 0.0763 1.0000 8.750 1.0424 0.01164 0.00540 -0.0060 0.0751 1.0000 9.000 1.0695 0.01185 0.00564 -0.0055 0.0746 1.0000 9.250 1.0964 0.01208 0.00588 -0.0050 0.0740 1.0000 9.500 1.1232 0.01232 0.00614 -0.0045 0.0733 1.0000 9.750 1.1497 0.01257 0.00641 -0.0040 0.0725 1.0000 10.000 1.1762 0.01283 0.00670 -0.0035 0.0716 1.0000 10.250 1.2024 0.01311 0.00699 -0.0029 0.0708 1.0000 10.500 1.2284 0.01340 0.00730 -0.0023 0.0699 1.0000 10.750 1.2542 0.01370 0.00761 -0.0017 0.0689 1.0000 11.000 1.2797 0.01403 0.00795 -0.0011 0.0679 1.0000 11.250 1.3048 0.01440 0.00834 -0.0005 0.0668 1.0000 11.500 1.3294 0.01482 0.00880 0.0002 0.0658 1.0000 11.750 1.3546 0.01513 0.00915 0.0009 0.0655 1.0000 12.000 1.3796 0.01545 0.00952 0.0016 0.0652 1.0000 12.250 1.4043 0.01579 0.00990 0.0023 0.0648 1.0000 12.500 1.4289 0.01612 0.01029 0.0030 0.0643 1.0000 12.750 1.4533 0.01646 0.01066 0.0037 0.0635 1.0000 13.000 1.4773 0.01681 0.01106 0.0045 0.0627 1.0000 13.250 1.5010 0.01719 0.01147 0.0053 0.0618 1.0000 13.500 1.5243 0.01758 0.01189 0.0061 0.0610 1.0000 13.750 1.5472 0.01799 0.01233 0.0069 0.0600 1.0000 14.000 1.5694 0.01846 0.01282 0.0079 0.0589 1.0000 14.250 1.5904 0.01901 0.01342 0.0089 0.0579 1.0000 14.500 1.6115 0.01951 0.01398 0.0099 0.0573 1.0000 14.750 1.6332 0.01992 0.01446 0.0109 0.0568 1.0000 15.000 1.6544 0.02036 0.01496 0.0119 0.0562 1.0000 15.250 1.6749 0.02082 0.01549 0.0130 0.0553 1.0000 15.500 1.6948 0.02130 0.01602 0.0142 0.0542 1.0000 15.750 1.7137 0.02183 0.01658 0.0154 0.0530 1.0000 16.000 1.7311 0.02243 0.01721 0.0167 0.0518 1.0000 16.250 1.7454 0.02311 0.01794 0.0185 0.0506 1.0000 16.500 1.7579 0.02380 0.01870 0.0204 0.0497 1.0000 16.750 1.7710 0.02450 0.01947 0.0222 0.0489 1.0000 17.000 1.7829 0.02530 0.02035 0.0239 0.0479 1.0000 17.250 1.7939 0.02621 0.02133 0.0255 0.0467 1.0000 17.500 1.8034 0.02728 0.02245 0.0270 0.0454 1.0000 17.750 1.8110 0.02857 0.02379 0.0284 0.0439 1.0000 18.000 1.8184 0.02994 0.02524 0.0296 0.0425 1.0000 18.250 1.8244 0.03152 0.02689 0.0306 0.0406 1.0000 18.500 1.8262 0.03359 0.02901 0.0314 0.0382 1.0000 18.750 1.8264 0.03597 0.03146 0.0317 0.0362 1.0000 19.000 1.8226 0.03892 0.03449 0.0317 0.0337 1.0000 19.250 1.8129 0.04281 0.03847 0.0308 0.0315 1.0000