XFOIL Version 6.96 Calculated polar for: NREL's S808 Airfoil 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.500 -0.9522 0.09042 0.08643 -0.0491 1.0000 0.0557 -17.250 -0.9570 0.08713 0.08312 -0.0499 1.0000 0.0585 -17.000 -0.9695 0.08288 0.07884 -0.0510 1.0000 0.0613 -16.750 -0.9768 0.07939 0.07533 -0.0518 1.0000 0.0644 -16.500 -0.9897 0.07526 0.07117 -0.0528 1.0000 0.0672 -16.250 -1.0010 0.07143 0.06732 -0.0536 1.0000 0.0706 -16.000 -1.0143 0.06743 0.06328 -0.0543 1.0000 0.0737 -15.750 -1.0321 0.06305 0.05887 -0.0552 1.0000 0.0769 -15.500 -1.0472 0.05912 0.05491 -0.0557 1.0000 0.0809 -15.250 -1.0661 0.05490 0.05065 -0.0562 1.0000 0.0837 -15.000 -1.0879 0.05056 0.04626 -0.0566 1.0000 0.0875 -14.750 -1.1047 0.04643 0.04208 -0.0575 0.9998 0.0909 -14.500 -1.1259 0.04113 0.03673 -0.0603 0.9988 0.0966 -14.250 -1.1383 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0.9421 0.2276 -9.500 -0.7439 0.01028 0.00570 -0.0971 0.9359 0.2295 -9.250 -0.7149 0.01005 0.00546 -0.0974 0.9290 0.2315 -9.000 -0.6835 0.00983 0.00522 -0.0981 0.9182 0.2335 -8.750 -0.6486 0.00961 0.00495 -0.0995 0.9015 0.2353 -8.500 -0.6137 0.00946 0.00466 -0.1008 0.8707 0.2368 -8.250 -0.5853 0.00943 0.00446 -0.1008 0.8347 0.2382 -8.000 -0.5590 0.00943 0.00431 -0.1004 0.8051 0.2393 -7.750 -0.5323 0.00942 0.00418 -0.1001 0.7791 0.2403 -7.500 -0.5057 0.00936 0.00403 -0.0999 0.7562 0.2423 -7.250 -0.4788 0.00930 0.00388 -0.0997 0.7350 0.2447 -7.000 -0.4514 0.00925 0.00376 -0.0996 0.7159 0.2470 -6.750 -0.4238 0.00921 0.00364 -0.0996 0.6980 0.2489 -6.500 -0.3959 0.00918 0.00354 -0.0995 0.6810 0.2508 -6.250 -0.3678 0.00915 0.00344 -0.0995 0.6649 0.2525 -6.000 -0.3393 0.00912 0.00334 -0.0995 0.6498 0.2541 -5.750 -0.3108 0.00911 0.00325 -0.0996 0.6353 0.2554 -5.500 -0.2824 0.00909 0.00316 -0.0996 0.6212 0.2569 -5.250 -0.2536 0.00903 0.00306 -0.0997 0.6073 0.2594 -5.000 -0.2248 0.00899 0.00298 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-0.1020 0.3932 0.3083 0.500 0.4161 0.00931 0.00255 -0.1022 0.3775 0.3150 0.750 0.4449 0.00937 0.00259 -0.1022 0.3690 0.3182 1.000 0.4737 0.00944 0.00264 -0.1022 0.3614 0.3208 1.250 0.5026 0.00951 0.00268 -0.1022 0.3540 0.3229 1.500 0.5311 0.00960 0.00274 -0.1022 0.3461 0.3256 1.750 0.5601 0.00964 0.00279 -0.1022 0.3391 0.3291 2.000 0.5885 0.00973 0.00286 -0.1022 0.3314 0.3324 2.250 0.6171 0.00981 0.00293 -0.1022 0.3249 0.3360 2.500 0.6456 0.00990 0.00301 -0.1021 0.3172 0.3393 2.750 0.6735 0.01002 0.00310 -0.1020 0.3097 0.3420 3.000 0.7022 0.01008 0.00317 -0.1020 0.3043 0.3462 3.250 0.7303 0.01019 0.00327 -0.1019 0.2968 0.3500 3.500 0.7581 0.01031 0.00337 -0.1017 0.2900 0.3537 3.750 0.7863 0.01040 0.00347 -0.1016 0.2843 0.3575 4.000 0.8137 0.01054 0.00358 -0.1014 0.2769 0.3608 4.250 0.8416 0.01065 0.00370 -0.1012 0.2710 0.3660 4.500 0.8693 0.01076 0.00382 -0.1010 0.2650 0.3706 4.750 0.8962 0.01093 0.00397 -0.1007 0.2579 0.3747 5.000 0.9236 0.01106 0.00409 -0.1005 0.2527 0.3782 5.250 0.9508 0.01119 0.00423 -0.1002 0.2468 0.3836 5.500 0.9772 0.01137 0.00440 -0.0998 0.2400 0.3893 5.750 1.0042 0.01150 0.00455 -0.0995 0.2350 0.3943 6.250 1.0563 0.01187 0.00490 -0.0986 0.2225 0.4036 6.500 1.0827 0.01202 0.00507 -0.0982 0.2177 0.4092 6.750 1.1082 0.01222 0.00526 -0.0977 0.2116 0.4148 7.000 1.1332 0.01243 0.00547 -0.0971 0.2059 0.4204 7.250 1.1588 0.01260 0.00567 -0.0966 0.2011 0.4271 7.500 1.1831 0.01283 0.00589 -0.0958 0.1950 0.4328 8.000 1.2315 0.01327 0.00635 -0.0943 0.1849 0.4439 8.250 1.2539 0.01353 0.00660 -0.0933 0.1792 0.4502 8.500 1.2754 0.01376 0.00685 -0.0920 0.1746 0.4562 8.750 1.2970 0.01397 0.00709 -0.0908 0.1702 0.4636 9.000 1.3174 0.01426 0.00738 -0.0894 0.1654 0.4711 9.250 1.3375 0.01457 0.00769 -0.0880 0.1607 0.4769 9.500 1.3587 0.01483 0.00799 -0.0868 0.1567 0.4839 9.750 1.3783 0.01516 0.00833 -0.0854 0.1522 0.4912 10.000 1.3971 0.01554 0.00870 -0.0838 0.1477 0.4975 10.250 1.4174 0.01584 0.00905 -0.0826 0.1441 0.5060 10.500 1.4359 0.01622 0.00945 -0.0811 0.1398 0.5147 10.750 1.4529 0.01668 0.00991 -0.0794 0.1352 0.5225 11.000 1.4719 0.01704 0.01032 -0.0780 0.1319 0.5312 11.250 1.4890 0.01749 0.01078 -0.0764 0.1281 0.5386 11.500 1.5045 0.01802 0.01134 -0.0746 0.1238 0.5477 11.750 1.5212 0.01850 0.01185 -0.0731 0.1208 0.5577 12.000 1.5370 0.01903 0.01242 -0.0714 0.1172 0.5675 12.250 1.5509 0.01966 0.01308 -0.0696 0.1136 0.5769 12.500 1.5649 0.02031 0.01377 -0.0679 0.1104 0.5866 12.750 1.5789 0.02097 0.01447 -0.0663 0.1073 0.5980 13.000 1.5912 0.02175 0.01529 -0.0645 0.1040 0.6087 13.250 1.6014 0.02267 0.01624 -0.0627 0.1007 0.6196 13.500 1.6140 0.02349 0.01713 -0.0612 0.0983 0.6319 13.750 1.6242 0.02449 0.01818 -0.0595 0.0952 0.6448 14.000 1.6320 0.02569 0.01943 -0.0579 0.0921 0.6586 14.250 1.6413 0.02685 0.02066 -0.0565 0.0898 0.6733 14.500 1.6505 0.02808 0.02197 -0.0552 0.0875 0.6891 14.750 1.6572 0.02955 0.02351 -0.0540 0.0849 0.7069 15.000 1.6620 0.03124 0.02528 -0.0528 0.0825 0.7274 15.250 1.6690 0.03283 0.02697 -0.0518 0.0807 0.7514 15.500 1.6750 0.03456 0.02883 -0.0510 0.0786 0.7826 15.750 1.6781 0.03655 0.03098 -0.0502 0.0765 0.8330 16.000 1.6740 0.03855 0.03324 -0.0485 0.0747 1.0000 16.250 1.6763 0.04093 0.03567 -0.0481 0.0730 1.0000 16.500 1.6792 0.04334 0.03814 -0.0479 0.0715 1.0000 16.750 1.6792 0.04612 0.04097 -0.0478 0.0695 1.0000 17.000 1.6771 0.04923 0.04413 -0.0479 0.0678 1.0000 17.250 1.6727 0.05270 0.04765 -0.0483 0.0660 1.0000 17.500 1.6721 0.05584 0.05088 -0.0487 0.0647 1.0000 17.750 1.6693 0.05933 0.05443 -0.0493 0.0633 1.0000 18.000 1.6638 0.06325 0.05842 -0.0502 0.0617 1.0000 18.250 1.6563 0.06755 0.06279 -0.0513 0.0603 1.0000 18.500 1.6479 0.07206 0.06737 -0.0526 0.0589 1.0000 18.750 1.6428 0.07624 0.07164 -0.0539 0.0579 1.0000 19.000 1.6366 0.08066 0.07614 -0.0553 0.0568 1.0000 19.250 1.6281 0.08549 0.08104 -0.0571 0.0554 1.0000