XFOIL Version 6.96 Calculated polar for: NREL's S825 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.4982 0.07420 0.07066 -0.0603 1.0000 0.0302 -11.000 -0.5177 0.06905 0.06546 -0.0610 1.0000 0.0296 -10.750 -0.5417 0.06364 0.05996 -0.0616 1.0000 0.0289 -10.500 -0.6214 0.05345 0.04923 -0.0634 1.0000 0.0251 -10.250 -0.6173 0.05053 0.04628 -0.0617 1.0000 0.0240 -10.000 -0.6332 0.04717 0.04285 -0.0604 1.0000 0.0237 -9.750 -0.7490 0.05656 0.05189 -0.0602 1.0000 0.0255 -9.500 -0.7411 0.05429 0.04957 -0.0582 1.0000 0.0238 -9.250 -0.7460 0.05103 0.04619 -0.0580 1.0000 0.0231 -9.000 -0.7473 0.04749 0.04244 -0.0581 1.0000 0.0223 -8.750 -0.7448 0.04363 0.03826 -0.0575 1.0000 0.0214 -8.500 -0.7380 0.04053 0.03484 -0.0558 1.0000 0.0208 -8.250 -0.7266 0.03852 0.03263 -0.0538 0.9997 0.0208 -8.000 -0.6952 0.03714 0.03109 -0.0539 0.9954 0.0213 -7.750 -0.6646 0.03629 0.03012 -0.0533 0.9904 0.0221 -7.500 -0.6292 0.03543 0.02909 -0.0552 0.9852 0.0241 -7.250 -0.6020 0.03528 0.02894 -0.0530 0.9795 0.0258 -7.000 -0.5686 0.03462 0.02834 -0.0548 0.9734 0.0289 -6.750 -0.5355 0.03428 0.02797 -0.0554 0.9677 0.0323 -6.500 -0.5017 0.03303 0.02681 -0.0590 0.9607 0.0383 -6.250 -0.4555 0.03136 0.02518 -0.0660 0.9572 0.0500 -6.000 -0.4104 0.02775 0.02170 -0.0768 0.9497 0.0703 -5.750 -0.2928 0.01989 0.01443 -0.1112 0.9568 0.3615 -5.500 -0.2676 0.02221 0.01690 -0.1078 0.9462 0.3785 -5.250 -0.2393 0.02410 0.01881 -0.1055 0.9373 0.3901 -5.000 -0.2227 0.02994 0.02508 -0.0934 0.9306 0.3942 -4.750 -0.1958 0.03103 0.02609 -0.0918 0.9209 0.4046 -4.500 -0.1846 0.04703 0.04254 -0.0548 0.9190 0.4377 -4.250 -0.1565 0.04261 0.03795 -0.0657 0.9080 0.4348 -4.000 -0.1161 0.04874 0.04414 -0.0496 0.9087 0.4701 -3.750 -0.0793 0.04688 0.04215 -0.0584 0.9034 0.4804 -3.500 0.0213 0.02870 0.02413 -0.0605 0.8768 0.4808 -3.250 0.0495 0.02735 0.02273 -0.0607 0.8695 0.4817 -3.000 0.0840 0.02598 0.02130 -0.0622 0.8638 0.4831 -2.750 0.1262 0.02441 0.01964 -0.0661 0.8601 0.4846 -2.500 0.1552 0.02320 0.01837 -0.0679 0.8486 0.4862 -2.250 0.1946 0.02184 0.01693 -0.0723 0.8391 0.4883 -2.000 0.2311 0.02011 0.01506 -0.0817 0.8261 0.4956 -1.750 0.2548 0.02595 0.02013 -0.1147 0.8461 0.4482 -1.500 0.2959 0.02518 0.01932 -0.1175 0.8344 0.4475 -1.250 0.3449 0.02418 0.01824 -0.1225 0.8222 0.4466 -1.000 0.3957 0.02288 0.01678 -0.1288 0.8073 0.4461 -0.750 0.4458 0.02140 0.01507 -0.1357 0.7902 0.4464 -0.500 0.4898 0.02026 0.01371 -0.1407 0.7724 0.4466 -0.250 0.5309 0.01929 0.01249 -0.1451 0.7548 0.4473 0.000 0.5677 0.01862 0.01158 -0.1482 0.7375 0.4482 0.250 0.5982 0.01826 0.01109 -0.1493 0.7206 0.4490 0.500 0.6268 0.01808 0.01083 -0.1498 0.7049 0.4498 0.750 0.6551 0.01798 0.01065 -0.1501 0.6906 0.4506 1.000 0.6833 0.01793 0.01053 -0.1504 0.6774 0.4514 1.250 0.7107 0.01788 0.01045 -0.1506 0.6646 0.4524 1.500 0.7384 0.01787 0.01041 -0.1508 0.6528 0.4537 1.750 0.7673 0.01788 0.01036 -0.1513 0.6422 0.4553 2.000 0.7966 0.01786 0.01029 -0.1519 0.6320 0.4573 2.250 0.8258 0.01780 0.01019 -0.1526 0.6222 0.4592 2.500 0.8578 0.01776 0.01004 -0.1539 0.6142 0.4611 2.750 0.8874 0.01770 0.00994 -0.1548 0.6050 0.4631 3.000 0.9176 0.01772 0.00991 -0.1556 0.5975 0.4647 3.250 0.9446 0.01777 0.01004 -0.1556 0.5896 0.4661 3.500 0.9740 0.01792 0.01019 -0.1561 0.5833 0.4677 3.750 1.0002 0.01801 0.01038 -0.1559 0.5756 0.4694 4.000 1.0301 0.01817 0.01050 -0.1565 0.5689 0.4715 4.250 1.0556 0.01823 0.01065 -0.1562 0.5602 0.4737 4.500 1.0846 0.01834 0.01072 -0.1566 0.5520 0.4765 4.750 1.1108 0.01840 0.01078 -0.1565 0.5421 0.4794 5.000 1.1361 0.01848 0.01095 -0.1561 0.5335 0.4815 5.250 1.1617 0.01860 0.01114 -0.1557 0.5249 0.4837 5.500 1.1863 0.01873 0.01137 -0.1551 0.5161 0.4863 5.750 1.2134 0.01886 0.01149 -0.1551 0.5076 0.4891 6.000 1.2370 0.01896 0.01170 -0.1544 0.4980 0.4922 6.250 1.2629 0.01908 0.01184 -0.1541 0.4890 0.4951 6.500 1.2854 0.01915 0.01203 -0.1531 0.4787 0.4974 6.750 1.3069 0.01927 0.01228 -0.1519 0.4678 0.5001 7.000 1.3287 0.01940 0.01248 -0.1507 0.4564 0.5033 7.250 1.3502 0.01954 0.01265 -0.1495 0.4443 0.5069 7.500 1.3697 0.01967 0.01285 -0.1480 0.4306 0.5105 7.750 1.3866 0.01980 0.01313 -0.1459 0.4156 0.5134 8.000 1.4019 0.01999 0.01343 -0.1436 0.3979 0.5169 8.250 1.4156 0.02022 0.01375 -0.1410 0.3766 0.5209 8.500 1.4251 0.02056 0.01406 -0.1377 0.3502 0.5248 8.750 1.4298 0.02108 0.01454 -0.1336 0.3118 0.5275 9.000 1.4283 0.02217 0.01541 -0.1289 0.2636 0.5302 9.500 1.4241 0.02524 0.01803 -0.1204 0.1870 0.5367 9.750 1.4238 0.02688 0.01950 -0.1167 0.1600 0.5402 10.000 1.4238 0.02852 0.02109 -0.1133 0.1385 0.5430 10.250 1.4229 0.03032 0.02285 -0.1100 0.1219 0.5462 10.500 1.4226 0.03221 0.02471 -0.1071 0.1081 0.5501 10.750 1.4237 0.03413 0.02663 -0.1046 0.0963 0.5545 11.000 1.4250 0.03611 0.02869 -0.1023 0.0864 0.5581 11.250 1.4228 0.03850 0.03113 -0.1001 0.0789 0.5619 11.500 1.4231 0.04082 0.03354 -0.0983 0.0718 0.5667 11.750 1.4222 0.04344 0.03623 -0.0968 0.0658 0.5712 12.000 1.4226 0.04601 0.03890 -0.0956 0.0603 0.5754 12.250 1.4194 0.04912 0.04208 -0.0944 0.0558 0.5800 12.500 1.4225 0.05172 0.04480 -0.0938 0.0508 0.5858 12.750 1.4170 0.05532 0.04842 -0.0931 0.0471 0.5897 13.000 1.4204 0.05811 0.05140 -0.0928 0.0433 0.5957 13.250 1.4215 0.06123 0.05462 -0.0928 0.0398 0.6019 13.500 1.4168 0.06508 0.05849 -0.0924 0.0368 0.6069 13.750 1.4200 0.06819 0.06181 -0.0926 0.0339 0.6148 14.000 1.4205 0.07164 0.06539 -0.0930 0.0314 0.6218 14.250 1.4176 0.07550 0.06922 -0.0927 0.0289 0.6297 14.500 1.4194 0.07901 0.07303 -0.0933 0.0270 0.6385 14.750 1.4197 0.08272 0.07689 -0.0940 0.0250 0.6489 15.000 1.4190 0.08655 0.08079 -0.0949 0.0234 0.6610 15.250 1.4182 0.09035 0.08473 -0.0951 0.0217 0.6738 15.500 1.4180 0.09428 0.08891 -0.0960 0.0204 0.6909 15.750 1.4178 0.09816 0.09300 -0.0969 0.0193 0.7142 16.000 1.4174 0.10198 0.09703 -0.0978 0.0184 0.7562 16.250 1.4135 0.10471 0.10002 -0.0973 0.0177 1.0000 16.500 1.4138 0.10871 0.10410 -0.0978 0.0169 1.0000 16.750 1.4090 0.11380 0.10941 -0.1000 0.0163 1.0000 17.000 1.4035 0.11906 0.11488 -0.1025 0.0157 1.0000 17.250 1.3990 0.12418 0.12017 -0.1049 0.0153 1.0000