XFOIL Version 6.96 Calculated polar for: SIKORSKY SC2110 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5343 0.08786 0.08581 -0.0134 1.0000 0.0174 -8.750 -0.5365 0.08022 0.07814 -0.0228 1.0000 0.0175 -8.500 -0.5385 0.07575 0.07365 -0.0255 0.9927 0.0176 -8.250 -0.5353 0.07191 0.06976 -0.0281 0.9838 0.0178 -8.000 -0.5336 0.06860 0.06640 -0.0291 0.9752 0.0179 -7.750 -0.5301 0.06535 0.06309 -0.0299 0.9683 0.0181 -7.500 -0.5267 0.06223 0.05988 -0.0300 0.9617 0.0183 -7.250 -0.5199 0.05891 0.05646 -0.0304 0.9558 0.0187 -7.000 -0.5133 0.05571 0.05314 -0.0300 0.9507 0.0191 -6.750 -0.5002 0.05191 0.04919 -0.0308 0.9460 0.0198 -6.500 -0.4857 0.04646 0.04307 -0.0294 0.9404 0.0215 -6.250 -0.4774 0.04157 0.03804 -0.0288 0.9367 0.0219 -6.000 -0.4585 0.03919 0.03562 -0.0291 0.9330 0.0222 -5.750 -0.4400 0.03720 0.03354 -0.0287 0.9292 0.0227 -5.500 -0.4217 0.03536 0.03158 -0.0279 0.9258 0.0234 -5.250 -0.4011 0.03320 0.02919 -0.0269 0.9228 0.0250 -5.000 -0.3771 0.02944 0.02485 -0.0260 0.9189 0.0271 -4.750 -0.3541 0.02756 0.02293 -0.0259 0.9154 0.0277 -4.500 -0.3312 0.02608 0.02135 -0.0253 0.9123 0.0286 -4.250 -0.3085 0.02467 0.01976 -0.0242 0.9095 0.0300 -4.000 -0.2818 0.02283 0.01744 -0.0234 0.9052 0.0334 -3.750 -0.2542 0.01861 0.01258 -0.0210 0.8999 0.0218 -3.500 -0.2332 0.01668 0.01060 -0.0191 0.8946 0.0206 -3.250 -0.2071 0.01531 0.00908 -0.0182 0.8885 0.0205 -3.000 -0.1818 0.01432 0.00797 -0.0171 0.8827 0.0208 -2.750 -0.1581 0.01364 0.00718 -0.0157 0.8781 0.0213 -2.500 -0.1313 0.01263 0.00619 -0.0154 0.8719 0.0226 -2.250 -0.1057 0.01214 0.00571 -0.0147 0.8659 0.0243 -2.000 -0.0806 0.01160 0.00512 -0.0137 0.8605 0.0255 -1.750 -0.0526 0.01107 0.00456 -0.0135 0.8533 0.0268 -1.500 -0.0269 0.01047 0.00396 -0.0128 0.8471 0.0292 -1.250 0.0014 0.01019 0.00368 -0.0127 0.8391 0.0325 -1.000 0.0284 0.00971 0.00317 -0.0123 0.8316 0.0373 -0.750 0.0571 0.00938 0.00284 -0.0123 0.8225 0.0465 -0.500 0.0814 0.00674 0.00241 -0.0129 0.8149 0.6801 -0.250 0.1064 0.00636 0.00247 -0.0118 0.8049 0.8071 0.000 0.1303 0.00626 0.00247 -0.0102 0.7937 0.8555 0.250 0.1522 0.00625 0.00250 -0.0081 0.7806 0.8913 0.500 0.1731 0.00627 0.00252 -0.0059 0.7647 0.9176 0.750 0.1928 0.00629 0.00249 -0.0033 0.7434 0.9366 1.000 0.2136 0.00629 0.00239 -0.0011 0.7130 0.9516 1.250 0.2383 0.00639 0.00225 -0.0001 0.6590 0.9619 1.500 0.2658 0.00690 0.00221 -0.0001 0.5380 0.9697 1.750 0.2958 0.00766 0.00235 -0.0012 0.4021 0.9762 2.000 0.3283 0.00808 0.00246 -0.0025 0.3456 0.9825 2.250 0.3635 0.00838 0.00255 -0.0043 0.3112 0.9867 2.500 0.3998 0.00862 0.00265 -0.0064 0.2847 0.9903 2.750 0.4360 0.00888 0.00276 -0.0084 0.2638 0.9939 3.000 0.4734 0.00910 0.00287 -0.0107 0.2469 0.9961 3.500 0.5371 0.00948 0.00309 -0.0129 0.2205 1.0000 3.750 0.5605 0.00964 0.00320 -0.0123 0.2108 1.0000 4.000 0.5845 0.00987 0.00334 -0.0118 0.2015 1.0000 4.250 0.6106 0.01003 0.00348 -0.0117 0.1938 1.0000 4.500 0.6373 0.01030 0.00367 -0.0117 0.1854 1.0000 4.750 0.6651 0.01047 0.00383 -0.0119 0.1782 1.0000 5.000 0.6926 0.01078 0.00406 -0.0122 0.1706 1.0000 5.250 0.7209 0.01096 0.00425 -0.0124 0.1649 1.0000 5.500 0.7486 0.01125 0.00448 -0.0127 0.1585 1.0000 5.750 0.7766 0.01150 0.00473 -0.0129 0.1530 1.0000 6.000 0.8046 0.01174 0.00496 -0.0132 0.1474 1.0000 6.250 0.8316 0.01216 0.00531 -0.0134 0.1417 1.0000 6.500 0.8597 0.01235 0.00555 -0.0136 0.1380 1.0000 6.750 0.8872 0.01262 0.00583 -0.0138 0.1337 1.0000 7.000 0.9137 0.01308 0.00622 -0.0139 0.1284 1.0000 7.250 0.9412 0.01331 0.00651 -0.0141 0.1251 1.0000 7.500 0.9685 0.01358 0.00682 -0.0142 0.1215 1.0000 7.750 0.9951 0.01395 0.00717 -0.0143 0.1178 1.0000 8.000 1.0205 0.01450 0.00771 -0.0143 0.1139 1.0000 8.250 1.0476 0.01474 0.00803 -0.0144 0.1112 1.0000 8.500 1.0742 0.01504 0.00837 -0.0145 0.1079 1.0000 8.750 1.0999 0.01545 0.00877 -0.0144 0.1048 1.0000 9.000 1.1236 0.01617 0.00949 -0.0142 0.1012 1.0000 9.250 1.1500 0.01645 0.00986 -0.0142 0.0992 1.0000 9.500 1.1757 0.01679 0.01026 -0.0142 0.0965 1.0000 9.750 1.2009 0.01718 0.01069 -0.0141 0.0938 1.0000 10.000 1.2244 0.01778 0.01129 -0.0139 0.0910 1.0000 10.250 1.2475 0.01844 0.01201 -0.0135 0.0883 1.0000 10.500 1.2727 0.01873 0.01239 -0.0135 0.0859 1.0000 10.750 1.2971 0.01909 0.01282 -0.0133 0.0833 1.0000 11.000 1.3202 0.01958 0.01333 -0.0130 0.0808 1.0000 11.250 1.3396 0.02055 0.01430 -0.0123 0.0777 1.0000 11.500 1.3639 0.02080 0.01469 -0.0122 0.0759 1.0000 11.750 1.3870 0.02119 0.01517 -0.0119 0.0735 1.0000 12.000 1.4088 0.02167 0.01570 -0.0115 0.0712 1.0000 12.250 1.4280 0.02236 0.01641 -0.0108 0.0687 1.0000 12.500 1.4463 0.02314 0.01727 -0.0100 0.0664 1.0000 12.750 1.4676 0.02355 0.01781 -0.0095 0.0643 1.0000 13.000 1.4877 0.02399 0.01832 -0.0090 0.0618 1.0000 13.250 1.5023 0.02471 0.01906 -0.0078 0.0594 1.0000 13.500 1.5132 0.02576 0.02017 -0.0063 0.0573 1.0000 13.750 1.5305 0.02637 0.02092 -0.0055 0.0556 1.0000 14.000 1.5462 0.02709 0.02176 -0.0046 0.0535 1.0000 14.250 1.5595 0.02800 0.02273 -0.0036 0.0513 1.0000 14.500 1.5666 0.02941 0.02417 -0.0022 0.0489 1.0000 14.750 1.5826 0.03018 0.02509 -0.0016 0.0469 1.0000 15.000 1.5949 0.03125 0.02625 -0.0008 0.0441 1.0000 15.250 1.6009 0.03289 0.02792 0.0002 0.0412 1.0000 15.500 1.6120 0.03413 0.02929 0.0009 0.0380 1.0000 15.750 1.6143 0.03623 0.03143 0.0016 0.0343 1.0000 16.000 1.6160 0.03847 0.03377 0.0023 0.0297 1.0000 16.250 1.6097 0.04167 0.03705 0.0026 0.0255 1.0000 16.500 1.5969 0.04581 0.04130 0.0024 0.0222 1.0000 16.750 1.5814 0.05071 0.04633 0.0013 0.0200 1.0000 17.000 1.5603 0.05696 0.05275 -0.0012 0.0190 1.0000 17.250 1.5359 0.06456 0.06055 -0.0051 0.0185 1.0000 17.500 1.5058 0.07410 0.07033 -0.0106 0.0188 1.0000 17.750 1.4734 0.08436 0.08083 -0.0163 0.0196 1.0000 18.000 1.4372 0.09488 0.09157 -0.0217 0.0208 1.0000 18.250 1.3987 0.10556 0.10242 -0.0271 0.0227 1.0000