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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.500 -0.5040 0.09252 0.08896 -0.0056 1.0000 0.0355 -7.250 -0.5022 0.08842 0.08489 -0.0083 1.0000 0.0358 -6.750 -0.5226 0.06984 0.06617 -0.0272 1.0000 0.0283 -6.250 -0.5212 0.05526 0.05118 -0.0331 1.0000 0.0241 -6.000 -0.5104 0.05165 0.04745 -0.0336 1.0000 0.0239 -5.750 -0.4988 0.04766 0.04328 -0.0339 1.0000 0.0238 -5.500 -0.4866 0.04344 0.03883 -0.0338 1.0000 0.0237 -5.250 -0.4788 0.03596 0.03064 -0.0330 1.0000 0.0241 -5.000 -0.4620 0.03419 0.02880 -0.0321 1.0000 0.0244 -4.750 -0.4485 0.03013 0.02422 -0.0304 1.0000 0.0243 -4.500 -0.4320 0.02755 0.02130 -0.0288 1.0000 0.0243 -4.250 -0.4143 0.02559 0.01908 -0.0272 1.0000 0.0244 -4.000 -0.3958 0.02399 0.01727 -0.0256 1.0000 0.0246 -3.750 -0.3657 0.02240 0.01547 -0.0261 0.9966 0.0250 -3.500 -0.3310 0.02092 0.01376 -0.0273 0.9923 0.0254 -3.250 -0.2958 0.01957 0.01220 -0.0285 0.9874 0.0260 -3.000 -0.2584 0.01831 0.01075 -0.0300 0.9831 0.0267 -2.750 -0.2199 0.01724 0.00948 -0.0315 0.9748 0.0279 -2.500 -0.1824 0.01636 0.00854 -0.0329 0.9632 0.0293 -2.250 -0.1504 0.01572 0.00789 -0.0332 0.9499 0.0304 -2.000 -0.1210 0.01506 0.00720 -0.0329 0.9380 0.0315 -1.750 -0.0924 0.01445 0.00656 -0.0324 0.9261 0.0327 -1.500 -0.0647 0.01389 0.00598 -0.0317 0.9133 0.0339 -1.250 -0.0376 0.01347 0.00561 -0.0310 0.8997 0.0360 -1.000 -0.0112 0.01312 0.00523 -0.0300 0.8846 0.0387 -0.750 0.0145 0.01272 0.00483 -0.0289 0.8674 0.0411 -0.500 0.0397 0.01241 0.00448 -0.0276 0.8430 0.0443 -0.250 0.0643 0.01214 0.00414 -0.0260 0.8118 0.0494 0.000 0.0893 0.01191 0.00382 -0.0246 0.7766 0.0569 0.250 0.1149 0.01169 0.00355 -0.0235 0.7417 0.0721 0.500 0.1404 0.01145 0.00333 -0.0224 0.7015 0.1154 0.750 0.1646 0.01076 0.00311 -0.0216 0.6547 0.2994 1.000 0.1772 0.00928 0.00320 -0.0179 0.6104 0.7794 1.250 0.1947 0.00934 0.00329 -0.0141 0.5591 0.9040 1.500 0.2294 0.00962 0.00327 -0.0142 0.4988 0.9714 1.750 0.2864 0.01002 0.00324 -0.0194 0.4300 1.0000 2.000 0.3102 0.01026 0.00322 -0.0184 0.3918 1.0000 2.250 0.3340 0.01051 0.00323 -0.0174 0.3582 1.0000 2.750 0.3826 0.01101 0.00332 -0.0156 0.3020 1.0000 3.000 0.4075 0.01127 0.00340 -0.0147 0.2771 1.0000 3.250 0.4329 0.01152 0.00349 -0.0140 0.2535 1.0000 3.500 0.4585 0.01180 0.00360 -0.0133 0.2312 1.0000 3.750 0.4843 0.01209 0.00373 -0.0126 0.2113 1.0000 4.000 0.5102 0.01238 0.00389 -0.0120 0.1947 1.0000 4.250 0.5363 0.01270 0.00408 -0.0113 0.1816 1.0000 4.500 0.5625 0.01298 0.00428 -0.0107 0.1713 1.0000 4.750 0.5888 0.01329 0.00450 -0.0101 0.1630 1.0000 5.000 0.6151 0.01360 0.00475 -0.0095 0.1552 1.0000 5.250 0.6414 0.01393 0.00501 -0.0089 0.1487 1.0000 5.500 0.6677 0.01424 0.00528 -0.0084 0.1423 1.0000 5.750 0.6935 0.01463 0.00558 -0.0077 0.1370 1.0000 6.000 0.7200 0.01493 0.00590 -0.0071 0.1327 1.0000 6.250 0.7461 0.01528 0.00622 -0.0065 0.1285 1.0000 6.500 0.7718 0.01568 0.00658 -0.0059 0.1248 1.0000 6.750 0.7975 0.01611 0.00698 -0.0053 0.1217 1.0000 7.000 0.8234 0.01648 0.00737 -0.0046 0.1186 1.0000 7.250 0.8492 0.01686 0.00777 -0.0040 0.1154 1.0000 7.500 0.8746 0.01729 0.00818 -0.0034 0.1126 1.0000 7.750 0.8992 0.01783 0.00866 -0.0027 0.1101 1.0000 8.000 0.9245 0.01830 0.00917 -0.0020 0.1082 1.0000 8.250 0.9497 0.01877 0.00970 -0.0013 0.1063 1.0000 8.500 0.9746 0.01926 0.01023 -0.0006 0.1044 1.0000 8.750 0.9993 0.01977 0.01077 0.0002 0.1026 1.0000 9.000 1.0237 0.02030 0.01134 0.0009 0.1009 1.0000 9.250 1.0478 0.02087 0.01192 0.0016 0.0994 1.0000 9.500 1.0711 0.02156 0.01259 0.0024 0.0978 1.0000 9.750 1.0948 0.02223 0.01332 0.0032 0.0964 1.0000 10.000 1.1186 0.02283 0.01403 0.0040 0.0950 1.0000 10.250 1.1419 0.02349 0.01478 0.0048 0.0937 1.0000 10.500 1.1649 0.02418 0.01558 0.0057 0.0925 1.0000 10.750 1.1875 0.02490 0.01638 0.0065 0.0913 1.0000 11.000 1.2098 0.02563 0.01719 0.0074 0.0902 1.0000 11.250 1.2317 0.02639 0.01803 0.0083 0.0892 1.0000 11.500 1.2531 0.02718 0.01889 0.0092 0.0883 1.0000 11.750 1.2740 0.02802 0.01979 0.0102 0.0874 1.0000 12.000 1.2943 0.02898 0.02078 0.0111 0.0864 1.0000 12.250 1.3139 0.03008 0.02197 0.0121 0.0854 1.0000 12.500 1.3322 0.03105 0.02314 0.0133 0.0845 1.0000 12.750 1.3496 0.03214 0.02443 0.0144 0.0837 1.0000 13.000 1.3658 0.03331 0.02579 0.0157 0.0829 1.0000 13.250 1.3808 0.03455 0.02722 0.0170 0.0820 1.0000 13.500 1.3944 0.03585 0.02869 0.0184 0.0812 1.0000 13.750 1.4064 0.03720 0.03021 0.0198 0.0805 1.0000 14.000 1.4167 0.03857 0.03174 0.0214 0.0797 1.0000 14.250 1.4240 0.03988 0.03319 0.0233 0.0790 1.0000 14.500 1.4302 0.04122 0.03465 0.0251 0.0782 1.0000 14.750 1.4358 0.04265 0.03619 0.0267 0.0776 1.0000 15.000 1.4410 0.04418 0.03782 0.0280 0.0769 1.0000 15.250 1.4466 0.04576 0.03947 0.0291 0.0762 1.0000 15.500 1.4503 0.04773 0.04151 0.0300 0.0754 1.0000 15.750 1.4415 0.05071 0.04473 0.0303 0.0747 1.0000 16.000 1.4274 0.05455 0.04885 0.0297 0.0741 1.0000 16.250 1.4086 0.05948 0.05406 0.0277 0.0735 1.0000 16.500 1.3831 0.06599 0.06085 0.0240 0.0729 1.0000 16.750 1.3419 0.07585 0.07100 0.0172 0.0725 1.0000