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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.000 -0.4938 0.08753 0.08407 -0.0097 1.0000 0.0520 -6.750 -0.5016 0.08104 0.07758 -0.0208 1.0000 0.0536 -6.500 -0.5130 0.07394 0.07009 -0.0316 1.0000 0.0545 -6.250 -0.4989 0.06962 0.06596 -0.0299 1.0000 0.0551 -6.000 -0.4865 0.06682 0.06321 -0.0290 1.0000 0.0559 -5.750 -0.4747 0.06394 0.06033 -0.0291 1.0000 0.0569 -5.500 -0.4628 0.06073 0.05708 -0.0298 1.0000 0.0585 -5.250 -0.4527 0.05775 0.05331 -0.0333 1.0000 0.0640 -5.000 -0.4417 0.05192 0.04765 -0.0332 1.0000 0.0650 -4.750 -0.4275 0.04921 0.04504 -0.0323 1.0000 0.0661 -4.500 -0.4140 0.04699 0.04282 -0.0311 1.0000 0.0676 -4.250 -0.4009 0.04481 0.04056 -0.0299 1.0000 0.0703 -4.000 -0.3894 0.04196 0.03719 -0.0285 1.0000 0.0767 -3.750 -0.3765 0.03964 0.03500 -0.0270 1.0000 0.0783 -3.500 -0.3630 0.03800 0.03336 -0.0254 1.0000 0.0813 -3.250 -0.3482 0.03635 0.03123 -0.0236 1.0000 0.0899 -3.000 -0.3339 0.03403 0.02900 -0.0222 1.0000 0.0919 -2.750 -0.3182 0.03248 0.02744 -0.0207 1.0000 0.0952 -2.500 -0.3006 0.03105 0.02568 -0.0194 1.0000 0.1053 -2.250 -0.2509 0.02307 0.01638 -0.0195 0.9968 0.0560 -2.000 -0.2069 0.02077 0.01378 -0.0216 0.9924 0.0518 -1.750 -0.1646 0.01902 0.01178 -0.0235 0.9872 0.0516 -1.500 -0.1202 0.01786 0.01040 -0.0258 0.9826 0.0533 -1.250 -0.0778 0.01673 0.00914 -0.0277 0.9763 0.0540 -1.000 -0.0324 0.01529 0.00775 -0.0304 0.9725 0.0561 -0.750 0.0091 0.01453 0.00708 -0.0324 0.9641 0.0606 -0.500 0.0498 0.01366 0.00625 -0.0339 0.9519 0.0659 -0.250 0.0845 0.01296 0.00564 -0.0341 0.9353 0.0729 0.000 0.1124 0.01234 0.00509 -0.0330 0.9175 0.0850 0.250 0.1370 0.01162 0.00454 -0.0314 0.8979 0.1224 0.500 0.1389 0.00890 0.00456 -0.0250 0.8793 0.8505 0.750 0.1645 0.00885 0.00453 -0.0217 0.8571 0.9631 1.000 0.2336 0.00877 0.00425 -0.0280 0.8264 1.0000 1.250 0.2550 0.00873 0.00401 -0.0259 0.7925 1.0000 1.500 0.2768 0.00874 0.00380 -0.0239 0.7520 1.0000 1.750 0.2990 0.00882 0.00362 -0.0221 0.7031 1.0000 2.000 0.3215 0.00900 0.00347 -0.0203 0.6455 1.0000 2.250 0.3438 0.00930 0.00339 -0.0187 0.5811 1.0000 2.500 0.3666 0.00965 0.00338 -0.0173 0.5175 1.0000 2.750 0.3897 0.01005 0.00342 -0.0161 0.4610 1.0000 3.000 0.4134 0.01046 0.00351 -0.0151 0.4125 1.0000 3.250 0.4379 0.01084 0.00363 -0.0141 0.3699 1.0000 3.500 0.4625 0.01126 0.00379 -0.0133 0.3305 1.0000 3.750 0.4874 0.01170 0.00397 -0.0125 0.2938 1.0000 4.000 0.5125 0.01215 0.00418 -0.0118 0.2622 1.0000 4.250 0.5382 0.01255 0.00443 -0.0111 0.2371 1.0000 4.500 0.5638 0.01299 0.00470 -0.0104 0.2189 1.0000 4.750 0.5895 0.01344 0.00501 -0.0097 0.2046 1.0000 5.000 0.6152 0.01392 0.00537 -0.0090 0.1930 1.0000 5.250 0.6405 0.01446 0.00576 -0.0084 0.1832 1.0000 5.500 0.6669 0.01485 0.00614 -0.0077 0.1750 1.0000 5.750 0.6922 0.01545 0.00660 -0.0070 0.1682 1.0000 6.000 0.7184 0.01594 0.00710 -0.0064 0.1626 1.0000 6.250 0.7445 0.01642 0.00754 -0.0057 0.1574 1.0000 6.500 0.7699 0.01717 0.00816 -0.0051 0.1526 1.0000 6.750 0.7961 0.01768 0.00872 -0.0044 0.1487 1.0000 7.000 0.8222 0.01816 0.00923 -0.0038 0.1446 1.0000 7.250 0.8481 0.01872 0.00977 -0.0032 0.1412 1.0000 7.500 0.8736 0.01960 0.01056 -0.0026 0.1381 1.0000 7.750 0.8993 0.02040 0.01142 -0.0019 0.1357 1.0000 8.000 0.9251 0.02103 0.01215 -0.0013 0.1333 1.0000 8.250 0.9507 0.02172 0.01294 -0.0006 0.1309 1.0000 8.500 0.9760 0.02241 0.01367 0.0000 0.1285 1.0000 8.750 1.0013 0.02312 0.01437 0.0007 0.1263 1.0000 9.000 1.0262 0.02420 0.01543 0.0012 0.1241 1.0000 9.250 1.0502 0.02559 0.01693 0.0018 0.1224 1.0000 9.500 1.0741 0.02647 0.01799 0.0026 0.1211 1.0000 9.750 1.0975 0.02751 0.01922 0.0034 0.1196 1.0000 10.000 1.1203 0.02866 0.02055 0.0043 0.1182 1.0000 10.250 1.1426 0.02989 0.02194 0.0051 0.1168 1.0000 10.500 1.1646 0.03111 0.02329 0.0059 0.1154 1.0000 10.750 1.1862 0.03224 0.02455 0.0067 0.1140 1.0000 11.000 1.2076 0.03339 0.02579 0.0075 0.1126 1.0000 11.250 1.2283 0.03484 0.02732 0.0083 0.1114 1.0000 11.500 1.2468 0.03704 0.02964 0.0091 0.1104 1.0000 11.750 1.2594 0.04016 0.03303 0.0101 0.1095 1.0000 12.000 1.2706 0.04219 0.03540 0.0116 0.1089 1.0000 12.250 1.2780 0.04474 0.03830 0.0131 0.1083 1.0000 12.500 1.2799 0.04777 0.04169 0.0147 0.1076 1.0000 12.750 1.2738 0.05131 0.04561 0.0165 0.1067 1.0000 13.000 1.2568 0.05560 0.05027 0.0183 0.1062 1.0000 13.250 1.2209 0.06081 0.05578 0.0202 0.1061 1.0000 13.500 1.1523 0.07035 0.06566 0.0173 0.1068 1.0000 13.750 1.0288 0.09607 0.09164 -0.0011 0.1094 1.0000