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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.750 -0.5431 0.08703 0.08472 -0.0050 1.0000 0.0149 -7.500 -0.5479 0.08117 0.07889 -0.0096 1.0000 0.0148 -7.250 -0.5554 0.07452 0.07225 -0.0171 1.0000 0.0148 -7.000 -0.5553 0.06781 0.06548 -0.0237 1.0000 0.0149 -6.750 -0.5528 0.06137 0.05893 -0.0284 1.0000 0.0150 -6.500 -0.5505 0.05396 0.05133 -0.0321 1.0000 0.0149 -6.250 -0.5472 0.04584 0.04292 -0.0343 1.0000 0.0149 -6.000 -0.5426 0.03717 0.03380 -0.0349 1.0000 0.0150 -5.750 -0.5486 0.02346 0.01882 -0.0330 1.0000 0.0155 -5.500 -0.5271 0.02046 0.01536 -0.0323 0.9977 0.0157 -5.250 -0.4969 0.01857 0.01313 -0.0329 0.9933 0.0162 -5.000 -0.4664 0.01719 0.01148 -0.0334 0.9882 0.0166 -4.750 -0.4345 0.01607 0.01015 -0.0340 0.9837 0.0168 -4.500 -0.4040 0.01512 0.00905 -0.0343 0.9781 0.0170 -4.250 -0.3729 0.01431 0.00818 -0.0347 0.9728 0.0172 -4.000 -0.3449 0.01376 0.00760 -0.0344 0.9639 0.0175 -3.750 -0.3191 0.01330 0.00709 -0.0334 0.9489 0.0178 -3.500 -0.2955 0.01287 0.00660 -0.0320 0.9298 0.0182 -3.250 -0.2712 0.01245 0.00611 -0.0307 0.9125 0.0186 -3.000 -0.2458 0.01204 0.00564 -0.0296 0.9002 0.0191 -2.750 -0.2199 0.01165 0.00518 -0.0287 0.8870 0.0196 -2.500 -0.1936 0.01131 0.00477 -0.0278 0.8734 0.0200 -2.250 -0.1673 0.01094 0.00435 -0.0270 0.8592 0.0206 -2.000 -0.1408 0.01063 0.00402 -0.0262 0.8443 0.0212 -1.750 -0.1139 0.01041 0.00375 -0.0255 0.8274 0.0220 -1.500 -0.0871 0.01023 0.00349 -0.0247 0.8048 0.0232 -1.250 -0.0605 0.01010 0.00322 -0.0238 0.7720 0.0242 -1.000 -0.0340 0.00996 0.00294 -0.0230 0.7298 0.0255 -0.750 -0.0068 0.00991 0.00273 -0.0224 0.6869 0.0269 -0.500 0.0206 0.00990 0.00254 -0.0218 0.6416 0.0284 -0.250 0.0480 0.00991 0.00238 -0.0213 0.5916 0.0307 0.000 0.0755 0.00999 0.00226 -0.0208 0.5397 0.0337 0.250 0.1032 0.01007 0.00217 -0.0204 0.4879 0.0383 0.750 0.1587 0.01021 0.00205 -0.0197 0.3973 0.0655 1.000 0.1865 0.01021 0.00203 -0.0194 0.3627 0.1003 1.250 0.2143 0.01013 0.00202 -0.0192 0.3332 0.1638 1.500 0.2396 0.00883 0.00196 -0.0194 0.3094 0.5884 1.750 0.2640 0.00839 0.00206 -0.0182 0.2893 0.7675 2.000 0.2852 0.00827 0.00218 -0.0160 0.2702 0.8700 2.250 0.3048 0.00833 0.00227 -0.0133 0.2496 0.9282 2.500 0.3290 0.00847 0.00231 -0.0118 0.2265 0.9671 2.750 0.3678 0.00867 0.00235 -0.0135 0.2007 0.9882 3.250 0.4339 0.00905 0.00249 -0.0149 0.1708 1.0000 3.500 0.4599 0.00922 0.00257 -0.0142 0.1616 1.0000 4.000 0.5134 0.00958 0.00278 -0.0130 0.1447 1.0000 4.250 0.5405 0.00979 0.00290 -0.0125 0.1372 1.0000 4.500 0.5680 0.00996 0.00303 -0.0121 0.1321 1.0000 4.750 0.5954 0.01015 0.00316 -0.0116 0.1265 1.0000 5.000 0.6228 0.01036 0.00332 -0.0111 0.1218 1.0000 5.250 0.6504 0.01055 0.00347 -0.0107 0.1178 1.0000 5.500 0.6778 0.01076 0.00365 -0.0103 0.1136 1.0000 5.750 0.7051 0.01101 0.00384 -0.0098 0.1093 1.0000 6.000 0.7326 0.01120 0.00402 -0.0094 0.1065 1.0000 6.250 0.7600 0.01142 0.00422 -0.0089 0.1035 1.0000 6.500 0.7872 0.01167 0.00444 -0.0085 0.1007 1.0000 6.750 0.8141 0.01195 0.00469 -0.0080 0.0979 1.0000 7.000 0.8412 0.01220 0.00493 -0.0075 0.0961 1.0000 7.250 0.8683 0.01243 0.00518 -0.0070 0.0945 1.0000 7.500 0.8952 0.01269 0.00544 -0.0065 0.0927 1.0000 7.750 0.9220 0.01296 0.00572 -0.0060 0.0909 1.0000 8.000 0.9485 0.01326 0.00601 -0.0055 0.0892 1.0000 8.250 0.9748 0.01359 0.00633 -0.0049 0.0874 1.0000 8.500 1.0006 0.01398 0.00671 -0.0043 0.0855 1.0000 8.750 1.0270 0.01425 0.00702 -0.0038 0.0846 1.0000 9.000 1.0531 0.01456 0.00736 -0.0032 0.0835 1.0000 9.250 1.0790 0.01488 0.00772 -0.0026 0.0825 1.0000 9.500 1.1048 0.01522 0.00809 -0.0020 0.0814 1.0000 9.750 1.1302 0.01557 0.00847 -0.0013 0.0803 1.0000 10.000 1.1555 0.01594 0.00887 -0.0007 0.0792 1.0000 10.250 1.1804 0.01634 0.00929 0.0000 0.0782 1.0000 10.500 1.2048 0.01679 0.00976 0.0007 0.0772 1.0000 10.750 1.2285 0.01730 0.01029 0.0015 0.0761 1.0000 11.000 1.2516 0.01789 0.01092 0.0024 0.0751 1.0000 11.250 1.2758 0.01829 0.01139 0.0031 0.0746 1.0000 11.500 1.2998 0.01870 0.01187 0.0039 0.0740 1.0000 11.750 1.3234 0.01915 0.01239 0.0047 0.0732 1.0000 12.000 1.3464 0.01963 0.01294 0.0056 0.0725 1.0000 12.250 1.3690 0.02014 0.01352 0.0065 0.0718 1.0000 12.500 1.3912 0.02067 0.01411 0.0074 0.0712 1.0000 12.750 1.4129 0.02121 0.01473 0.0084 0.0705 1.0000 13.000 1.4341 0.02177 0.01536 0.0094 0.0698 1.0000 13.250 1.4548 0.02236 0.01601 0.0104 0.0692 1.0000 13.500 1.4748 0.02295 0.01666 0.0115 0.0684 1.0000 13.750 1.4937 0.02360 0.01735 0.0127 0.0675 1.0000 14.000 1.5105 0.02441 0.01820 0.0141 0.0663 1.0000 14.250 1.5277 0.02512 0.01900 0.0154 0.0655 1.0000 14.500 1.5458 0.02571 0.01970 0.0167 0.0648 1.0000 14.750 1.5607 0.02640 0.02050 0.0183 0.0642 1.0000 15.000 1.5737 0.02715 0.02135 0.0201 0.0635 1.0000 15.250 1.5862 0.02796 0.02226 0.0218 0.0627 1.0000 15.500 1.5982 0.02883 0.02322 0.0234 0.0619 1.0000 15.750 1.6093 0.02981 0.02431 0.0248 0.0612 1.0000 16.000 1.6194 0.03091 0.02549 0.0262 0.0604 1.0000 16.250 1.6284 0.03214 0.02680 0.0273 0.0597 1.0000 16.500 1.6358 0.03359 0.02833 0.0283 0.0590 1.0000 16.750 1.6409 0.03535 0.03017 0.0291 0.0582 1.0000 17.000 1.6428 0.03753 0.03244 0.0295 0.0575 1.0000 17.250 1.6486 0.03947 0.03452 0.0298 0.0570 1.0000 17.500 1.6530 0.04166 0.03687 0.0298 0.0564 1.0000 17.750 1.6557 0.04418 0.03952 0.0294 0.0556 1.0000 18.000 1.6565 0.04702 0.04251 0.0287 0.0549 1.0000 18.250 1.6557 0.05024 0.04586 0.0276 0.0540 1.0000 18.500 1.6525 0.05394 0.04969 0.0260 0.0531 1.0000 18.750 1.6457 0.05828 0.05415 0.0239 0.0523 1.0000 19.000 1.6349 0.06341 0.05940 0.0212 0.0516 1.0000 19.250 1.6184 0.06950 0.06561 0.0178 0.0510 1.0000