NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S802 Airfoil (s802-nr) Reynolds number: 100,000 Max Cl/Cd: 61.01 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s802-nr-100000.txt Download as CSV file: xf-s802-nr-100000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S802 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4227 0.10658 0.10234 -0.0326 1.0000 0.1026
-8.000 -0.4524 0.10629 0.10218 -0.0305 1.0000 0.1030
-7.750 -0.4803 0.10571 0.10170 -0.0284 1.0000 0.1032
-7.500 -0.4598 0.10015 0.09614 -0.0283 0.9979 0.1057
-7.250 -0.4330 0.09660 0.09253 -0.0291 0.9947 0.1106
-7.000 -0.4355 0.09290 0.08887 -0.0365 0.9862 0.1163
-6.750 -0.4356 0.08598 0.08194 -0.0493 0.9769 0.1200
-6.500 -0.4109 0.08457 0.08054 -0.0441 0.9747 0.1269
-6.250 -0.4104 0.07715 0.07298 -0.0592 0.9641 0.1351
-6.000 -0.3868 0.07529 0.07118 -0.0563 0.9615 0.1427
-5.750 -0.3837 0.07040 0.06618 -0.0624 0.9538 0.1517
-5.500 -0.3643 0.06592 0.06151 -0.0691 0.9489 0.1657
-5.250 -0.3498 0.06370 0.05934 -0.0669 0.9445 0.1711
-5.000 -0.3344 0.06018 0.05571 -0.0699 0.9390 0.1845
-4.750 -0.2713 0.04317 0.03687 -0.0884 0.9365 0.0927
-4.500 -0.2244 0.03747 0.02987 -0.0929 0.9348 0.0766
-4.250 -0.1965 0.03591 0.02786 -0.0934 0.9313 0.0758
-4.000 -0.1688 0.03369 0.02532 -0.0940 0.9276 0.0749
-3.750 -0.1352 0.03187 0.02312 -0.0954 0.9244 0.0749
-3.500 -0.0989 0.03033 0.02126 -0.0970 0.9218 0.0760
-3.250 -0.0626 0.02901 0.01998 -0.0990 0.9198 0.0819
-3.000 -0.0452 0.02858 0.01945 -0.0975 0.9153 0.0863
-2.750 -0.0183 0.02776 0.01862 -0.0975 0.9115 0.0916
-2.500 0.0142 0.02703 0.01795 -0.0986 0.9084 0.1049
-2.250 0.0517 0.02574 0.01719 -0.1009 0.9063 0.1780
-2.000 0.0715 0.02400 0.01783 -0.0994 0.9039 0.6521
-1.750 0.0724 0.02472 0.01865 -0.0935 0.8980 0.7612
-1.500 0.0759 0.02527 0.01924 -0.0872 0.8937 0.8256
-1.250 0.0860 0.02551 0.01940 -0.0821 0.8903 0.8728
-1.000 0.0800 0.02566 0.01954 -0.0756 0.8845 0.9050
-0.750 0.0928 0.02556 0.01939 -0.0721 0.8800 0.9534
-0.500 0.1442 0.02573 0.01934 -0.0772 0.8767 1.0000
-0.250 0.1724 0.02618 0.01960 -0.0785 0.8726 1.0000
0.000 0.1941 0.02666 0.01994 -0.0789 0.8670 1.0000
0.250 0.2294 0.02708 0.02020 -0.0812 0.8630 1.0000
0.500 0.2733 0.02748 0.02044 -0.0847 0.8599 1.0000
0.750 0.2853 0.02815 0.02104 -0.0836 0.8528 1.0000
1.000 0.3206 0.02859 0.02138 -0.0857 0.8480 1.0000
1.250 0.3653 0.02896 0.02164 -0.0890 0.8447 1.0000
1.500 0.3765 0.02974 0.02238 -0.0878 0.8364 1.0000
1.750 0.4157 0.03011 0.02268 -0.0902 0.8317 1.0000
2.000 0.4400 0.03077 0.02330 -0.0906 0.8247 1.0000
2.250 0.4712 0.03124 0.02374 -0.0919 0.8182 1.0000
2.500 0.5190 0.03137 0.02385 -0.0953 0.8144 1.0000
2.750 0.5313 0.03223 0.02470 -0.0939 0.8039 1.0000
3.000 0.5796 0.03221 0.02468 -0.0971 0.7996 1.0000
3.250 0.5948 0.03301 0.02549 -0.0961 0.7885 1.0000
3.500 0.6462 0.03270 0.02523 -0.0993 0.7843 1.0000
3.750 0.6633 0.03340 0.02595 -0.0983 0.7724 1.0000
4.000 0.7155 0.03282 0.02545 -0.1014 0.7677 1.0000
4.250 0.7391 0.03315 0.02583 -0.1009 0.7560 1.0000
4.500 0.7671 0.03328 0.02602 -0.1008 0.7448 1.0000
4.750 0.8278 0.03167 0.02455 -0.1041 0.7400 1.0000
5.000 0.8589 0.03134 0.02431 -0.1039 0.7282 1.0000
5.250 0.9380 0.02839 0.02155 -0.1091 0.7245 1.0000
5.500 0.9752 0.02742 0.02070 -0.1092 0.7122 1.0000
5.750 1.0224 0.02586 0.01928 -0.1105 0.7010 1.0000
6.000 1.0747 0.02398 0.01755 -0.1123 0.6891 1.0000
6.250 1.1105 0.02283 0.01652 -0.1121 0.6723 1.0000
6.500 1.1433 0.02177 0.01558 -0.1114 0.6525 1.0000
6.750 1.1727 0.02083 0.01475 -0.1102 0.6288 1.0000
7.000 1.1901 0.02038 0.01439 -0.1073 0.5980 1.0000
7.250 1.2032 0.02010 0.01414 -0.1038 0.5544 1.0000
7.500 1.2172 0.01995 0.01364 -0.1001 0.4790 1.0000
7.750 1.2176 0.02098 0.01400 -0.0950 0.3926 1.0000
8.000 1.2117 0.02265 0.01511 -0.0897 0.3234 1.0000
8.250 1.2081 0.02447 0.01646 -0.0852 0.2712 1.0000
8.500 1.2088 0.02628 0.01790 -0.0817 0.2314 1.0000
8.750 1.2141 0.02802 0.01935 -0.0789 0.2016 1.0000
9.000 1.2241 0.02966 0.02083 -0.0768 0.1782 1.0000
9.250 1.2369 0.03124 0.02226 -0.0751 0.1599 1.0000
9.500 1.2534 0.03280 0.02372 -0.0739 0.1449 1.0000
9.750 1.2740 0.03436 0.02524 -0.0732 0.1322 1.0000
10.000 1.2968 0.03597 0.02687 -0.0727 0.1214 1.0000
10.250 1.3290 0.03784 0.02865 -0.0736 0.1119 1.0000
10.500 1.3511 0.03946 0.03042 -0.0731 0.1044 1.0000
10.750 1.3832 0.04174 0.03279 -0.0740 0.0973 1.0000
11.000 1.4057 0.04372 0.03497 -0.0736 0.0919 1.0000
11.250 1.4378 0.04664 0.03795 -0.0750 0.0863 1.0000
11.500 1.4466 0.04888 0.04060 -0.0726 0.0830 1.0000
11.750 1.4598 0.05120 0.04316 -0.0712 0.0795 1.0000
12.000 1.4882 0.05511 0.04708 -0.0727 0.0749 1.0000
12.250 1.4780 0.05736 0.04978 -0.0682 0.0737 1.0000
12.500 1.4685 0.06031 0.05316 -0.0644 0.0725 1.0000
12.750 1.4568 0.06352 0.05676 -0.0610 0.0712 1.0000
13.000 1.4437 0.06692 0.06050 -0.0581 0.0699 1.0000
13.250 1.4308 0.07041 0.06427 -0.0557 0.0685 1.0000
13.500 1.4372 0.07295 0.06685 -0.0548 0.0658 1.0000
13.750 1.4352 0.07694 0.07095 -0.0539 0.0642 1.0000
14.000 1.4203 0.08256 0.07680 -0.0528 0.0635 1.0000
14.500 1.3709 0.09347 0.08827 -0.0516 0.0633 1.0000
14.750 1.3424 0.09879 0.09387 -0.0521 0.0636 1.0000
15.000 1.2175 0.11818 0.11399 -0.0621 0.0723 1.0000
15.250 1.1861 0.12870 0.12459 -0.0681 0.0737 1.0000
15.500 1.1625 0.13916 0.13510 -0.0741 0.0747 1.0000
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Polar data table (+)
Polar graphs
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