NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S802 Airfoil (s802-nr) Reynolds number: 50,000 Max Cl/Cd: 33.77 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s802-nr-50000-n5.txt Download as CSV file: xf-s802-nr-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3976 0.10333 0.09680 -0.0474 1.0000 0.0625
-8.500 -0.3890 0.10100 0.09450 -0.0438 1.0000 0.0610
-8.250 -0.3977 0.09899 0.09259 -0.0416 1.0000 0.0599
-8.000 -0.4110 0.09709 0.09079 -0.0393 1.0000 0.0590
-7.750 -0.4272 0.09530 0.08912 -0.0370 1.0000 0.0581
-7.500 -0.4276 0.09104 0.08490 -0.0407 0.9941 0.0565
-7.000 -0.4237 0.07228 0.06574 -0.0659 0.9718 0.0504
-6.750 -0.4137 0.06699 0.06021 -0.0705 0.9634 0.0504
-6.250 -0.3814 0.05946 0.05243 -0.0760 0.9504 0.0527
-6.000 -0.3631 0.05525 0.04789 -0.0793 0.9443 0.0534
-5.750 -0.3418 0.05076 0.04290 -0.0826 0.9382 0.0535
-5.500 -0.3121 0.04640 0.03795 -0.0865 0.9343 0.0535
-5.250 -0.2895 0.04332 0.03439 -0.0878 0.9282 0.0539
-5.000 -0.2599 0.04050 0.03108 -0.0898 0.9238 0.0549
-4.750 -0.2266 0.03823 0.02834 -0.0920 0.9206 0.0580
-4.500 -0.1996 0.03641 0.02597 -0.0926 0.9159 0.0610
-4.250 -0.1716 0.03475 0.02391 -0.0930 0.9114 0.0629
-4.000 -0.1414 0.03332 0.02236 -0.0938 0.9078 0.0655
-3.750 -0.1086 0.03218 0.02104 -0.0947 0.9050 0.0701
-3.500 -0.0881 0.03153 0.02014 -0.0934 0.8994 0.0759
-3.250 -0.0619 0.03075 0.01937 -0.0935 0.8953 0.0841
-3.000 -0.0318 0.02992 0.01847 -0.0940 0.8920 0.0954
-2.750 -0.0014 0.02911 0.01771 -0.0951 0.8886 0.1228
-2.500 0.0227 0.02821 0.01723 -0.0955 0.8836 0.1912
-2.250 0.0516 0.02659 0.01703 -0.0972 0.8805 0.4385
-2.000 0.0595 0.02651 0.01787 -0.0911 0.8764 0.6661
-1.750 0.0700 0.02700 0.01826 -0.0869 0.8709 0.7628
-1.500 0.0779 0.02728 0.01846 -0.0820 0.8653 0.8193
-1.250 0.0905 0.02729 0.01834 -0.0778 0.8613 0.8683
-1.000 0.1021 0.02727 0.01822 -0.0741 0.8562 0.9129
-0.500 0.1777 0.02738 0.01786 -0.0788 0.8479 1.0000
-0.250 0.2118 0.02762 0.01784 -0.0808 0.8449 1.0000
0.000 0.2283 0.02809 0.01816 -0.0801 0.8382 1.0000
0.250 0.2576 0.02846 0.01833 -0.0813 0.8338 1.0000
0.500 0.2924 0.02876 0.01845 -0.0832 0.8305 1.0000
0.750 0.3131 0.02932 0.01888 -0.0832 0.8243 1.0000
1.000 0.3414 0.02977 0.01920 -0.0841 0.8192 1.0000
1.250 0.3761 0.03011 0.01943 -0.0859 0.8155 1.0000
1.500 0.3972 0.03074 0.01997 -0.0858 0.8090 1.0000
1.750 0.4256 0.03121 0.02038 -0.0867 0.8036 1.0000
2.000 0.4616 0.03153 0.02063 -0.0885 0.7998 1.0000
2.250 0.4792 0.03228 0.02135 -0.0878 0.7918 1.0000
2.500 0.5112 0.03268 0.02172 -0.0890 0.7867 1.0000
2.750 0.5386 0.03320 0.02223 -0.0896 0.7806 1.0000
3.000 0.5631 0.03378 0.02282 -0.0898 0.7732 1.0000
3.250 0.6010 0.03397 0.02303 -0.0915 0.7690 1.0000
3.500 0.6167 0.03481 0.02390 -0.0905 0.7589 1.0000
4.000 0.6715 0.03570 0.02489 -0.0911 0.7434 1.0000
4.250 0.7121 0.03559 0.02489 -0.0928 0.7384 1.0000
4.500 0.7291 0.03632 0.02569 -0.0917 0.7267 1.0000
4.750 0.7544 0.03670 0.02616 -0.0914 0.7167 1.0000
5.250 0.8136 0.03680 0.02653 -0.0914 0.6968 1.0000
5.500 0.8397 0.03687 0.02674 -0.0908 0.6848 1.0000
5.750 0.8868 0.03567 0.02571 -0.0920 0.6774 1.0000
6.000 0.9116 0.03551 0.02574 -0.0909 0.6630 1.0000
6.250 0.9386 0.03510 0.02550 -0.0899 0.6480 1.0000
6.750 0.9766 0.03491 0.02567 -0.0860 0.6105 1.0000
7.000 0.9994 0.03441 0.02534 -0.0842 0.5898 1.0000
7.250 1.0116 0.03465 0.02575 -0.0817 0.5645 1.0000
7.500 1.0278 0.03462 0.02588 -0.0794 0.5357 1.0000
7.750 1.0521 0.03397 0.02535 -0.0776 0.5007 1.0000
8.000 1.0830 0.03289 0.02418 -0.0758 0.4519 1.0000
8.250 1.1062 0.03276 0.02368 -0.0738 0.3913 1.0000
8.500 1.1152 0.03395 0.02452 -0.0712 0.3387 1.0000
8.750 1.1193 0.03567 0.02594 -0.0687 0.2954 1.0000
9.000 1.1228 0.03757 0.02763 -0.0665 0.2604 1.0000
9.250 1.1272 0.03954 0.02942 -0.0646 0.2310 1.0000
9.500 1.1333 0.04150 0.03126 -0.0629 0.2062 1.0000
9.750 1.1404 0.04345 0.03310 -0.0614 0.1864 1.0000
10.000 1.1495 0.04534 0.03491 -0.0601 0.1691 1.0000
10.250 1.1611 0.04713 0.03670 -0.0590 0.1546 1.0000
10.500 1.1736 0.04889 0.03842 -0.0579 0.1418 1.0000
10.750 1.1886 0.05055 0.04020 -0.0570 0.1301 1.0000
11.000 1.2080 0.05209 0.04188 -0.0562 0.1200 1.0000
11.250 1.2269 0.05369 0.04352 -0.0555 0.1113 1.0000
11.500 1.2451 0.05540 0.04538 -0.0548 0.1036 1.0000
11.750 1.2674 0.05721 0.04738 -0.0542 0.0971 1.0000
12.000 1.2817 0.05930 0.04968 -0.0535 0.0912 1.0000
12.250 1.2999 0.06140 0.05184 -0.0530 0.0863 1.0000
12.500 1.3109 0.06428 0.05514 -0.0521 0.0824 1.0000
12.750 1.3184 0.06699 0.05808 -0.0513 0.0787 1.0000
13.000 1.3330 0.06930 0.06035 -0.0509 0.0750 1.0000
13.250 1.3259 0.07331 0.06488 -0.0499 0.0730 1.0000
13.500 1.3185 0.07762 0.06960 -0.0492 0.0713 1.0000
13.750 1.3082 0.08219 0.07451 -0.0489 0.0698 1.0000
14.000 1.2952 0.08703 0.07966 -0.0491 0.0684 1.0000
14.250 1.2808 0.09215 0.08505 -0.0497 0.0672 1.0000
14.500 1.2655 0.09755 0.09068 -0.0509 0.0662 1.0000
14.750 1.2491 0.10336 0.09669 -0.0527 0.0653 1.0000
15.000 1.2536 0.10651 0.09981 -0.0532 0.0633 1.0000
15.250 1.2266 0.11441 0.10798 -0.0569 0.0632 1.0000
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