NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S808 Airfoil (s808-nr) Reynolds number: 200,000 Max Cl/Cd: 56.04 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s808-nr-200000-n5.txt Download as CSV file: xf-s808-nr-200000-n5.csv |
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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7561 0.09680 0.09177 -0.0483 1.0000 0.1680
-15.250 -0.7904 0.08631 0.08121 -0.0518 1.0000 0.1821
-14.750 -0.8388 0.07458 0.06940 -0.0556 1.0000 0.1958
-14.500 -0.7905 0.07843 0.07328 -0.0532 1.0000 0.1950
-14.250 -0.9194 0.06000 0.05470 -0.0603 1.0000 0.2092
-14.000 -0.8495 0.06605 0.06082 -0.0569 1.0000 0.2084
-13.750 -0.7993 0.06996 0.06475 -0.0545 1.0000 0.2078
-13.500 -1.0264 0.04340 0.03788 -0.0633 1.0000 0.2225
-13.250 -1.0793 0.03740 0.03170 -0.0634 1.0000 0.2258
-13.000 -1.0623 0.03737 0.03174 -0.0620 1.0000 0.2284
-12.750 -1.0701 0.03554 0.02989 -0.0607 1.0000 0.2311
-12.500 -1.0935 0.03297 0.02725 -0.0587 1.0000 0.2339
-12.250 -1.1306 0.03046 0.02465 -0.0548 1.0000 0.2361
-12.000 -1.1535 0.02819 0.02220 -0.0526 1.0000 0.2388
-11.750 -1.1484 0.02726 0.02122 -0.0512 1.0000 0.2418
-11.500 -1.1292 0.02710 0.02111 -0.0505 0.9995 0.2450
-11.250 -1.0947 0.02669 0.02064 -0.0531 0.9958 0.2488
-11.000 -1.0607 0.02592 0.01972 -0.0562 0.9920 0.2523
-10.750 -1.0318 0.02491 0.01850 -0.0586 0.9870 0.2553
-10.500 -0.9982 0.02441 0.01796 -0.0605 0.9831 0.2575
-10.250 -0.9617 0.02410 0.01765 -0.0626 0.9800 0.2593
-10.000 -0.9290 0.02369 0.01720 -0.0641 0.9758 0.2612
-9.750 -0.8977 0.02324 0.01669 -0.0655 0.9706 0.2632
-9.500 -0.8623 0.02275 0.01612 -0.0676 0.9666 0.2656
-9.250 -0.8289 0.02220 0.01546 -0.0695 0.9623 0.2680
-9.000 -0.8007 0.02159 0.01473 -0.0704 0.9552 0.2700
-8.750 -0.7651 0.02099 0.01396 -0.0726 0.9509 0.2721
-8.500 -0.7358 0.02057 0.01358 -0.0731 0.9443 0.2737
-8.250 -0.7040 0.02022 0.01323 -0.0740 0.9376 0.2755
-8.000 -0.6666 0.01987 0.01287 -0.0761 0.9335 0.2777
-7.750 -0.6426 0.01949 0.01246 -0.0755 0.9224 0.2797
-7.500 -0.6066 0.01906 0.01198 -0.0773 0.9171 0.2820
-7.000 -0.5490 0.01818 0.01094 -0.0781 0.8968 0.2863
-6.750 -0.5171 0.01775 0.01039 -0.0790 0.8865 0.2885
-6.500 -0.4815 0.01735 0.01000 -0.0805 0.8773 0.2904
-6.250 -0.4426 0.01703 0.00969 -0.0825 0.8678 0.2926
-6.000 -0.4014 0.01673 0.00937 -0.0850 0.8571 0.2952
-5.750 -0.3572 0.01641 0.00898 -0.0881 0.8457 0.2980
-5.500 -0.3165 0.01610 0.00858 -0.0906 0.8302 0.3007
-5.250 -0.2766 0.01581 0.00816 -0.0929 0.8132 0.3034
-5.000 -0.2401 0.01558 0.00776 -0.0946 0.7949 0.3059
-4.750 -0.2071 0.01539 0.00754 -0.0954 0.7759 0.3081
-4.500 -0.1763 0.01528 0.00736 -0.0959 0.7574 0.3103
-4.250 -0.1467 0.01520 0.00720 -0.0961 0.7394 0.3128
-4.000 -0.1179 0.01514 0.00704 -0.0962 0.7222 0.3156
-3.750 -0.0897 0.01508 0.00686 -0.0962 0.7055 0.3186
-3.500 -0.0619 0.01500 0.00667 -0.0962 0.6893 0.3215
-3.250 -0.0341 0.01493 0.00649 -0.0961 0.6742 0.3240
-3.000 -0.0067 0.01487 0.00640 -0.0959 0.6597 0.3263
-2.750 0.0206 0.01483 0.00632 -0.0957 0.6452 0.3288
-2.500 0.0482 0.01480 0.00624 -0.0956 0.6315 0.3314
-2.250 0.0758 0.01478 0.00615 -0.0954 0.6187 0.3343
-2.000 0.1033 0.01477 0.00605 -0.0953 0.6053 0.3376
-1.750 0.1312 0.01475 0.00594 -0.0952 0.5929 0.3409
-1.500 0.1585 0.01474 0.00590 -0.0950 0.5811 0.3438
-1.250 0.1860 0.01472 0.00589 -0.0948 0.5689 0.3467
-1.000 0.2135 0.01474 0.00587 -0.0947 0.5577 0.3497
-0.750 0.2411 0.01476 0.00584 -0.0945 0.5461 0.3529
-0.500 0.2688 0.01477 0.00580 -0.0944 0.5355 0.3562
-0.250 0.2965 0.01481 0.00575 -0.0943 0.5245 0.3596
0.000 0.3239 0.01481 0.00578 -0.0941 0.5142 0.3628
0.250 0.3512 0.01486 0.00582 -0.0939 0.5038 0.3662
0.500 0.3789 0.01491 0.00586 -0.0937 0.4939 0.3701
0.750 0.4062 0.01498 0.00587 -0.0935 0.4839 0.3740
1.000 0.4339 0.01503 0.00589 -0.0934 0.4743 0.3778
1.250 0.4610 0.01509 0.00594 -0.0931 0.4648 0.3811
1.500 0.4883 0.01515 0.00603 -0.0929 0.4557 0.3847
1.750 0.5153 0.01525 0.00611 -0.0927 0.4462 0.3891
2.000 0.5426 0.01535 0.00619 -0.0925 0.4376 0.3937
2.250 0.5698 0.01545 0.00626 -0.0922 0.4285 0.3982
2.500 0.5964 0.01555 0.00638 -0.0919 0.4201 0.4020
2.750 0.6234 0.01564 0.00651 -0.0916 0.4113 0.4062
3.000 0.6496 0.01580 0.00662 -0.0913 0.4033 0.4111
3.250 0.6769 0.01591 0.00675 -0.0910 0.3947 0.4164
3.500 0.7029 0.01605 0.00690 -0.0906 0.3867 0.4210
3.750 0.7294 0.01619 0.00708 -0.0903 0.3790 0.4260
4.000 0.7556 0.01634 0.00725 -0.0899 0.3707 0.4312
4.250 0.7813 0.01654 0.00740 -0.0894 0.3635 0.4365
4.500 0.8075 0.01667 0.00762 -0.0890 0.3557 0.4415
4.750 0.8324 0.01688 0.00782 -0.0885 0.3483 0.4473
5.000 0.8583 0.01707 0.00803 -0.0880 0.3411 0.4539
5.250 0.8834 0.01726 0.00826 -0.0875 0.3336 0.4596
5.500 0.9075 0.01750 0.00851 -0.0868 0.3270 0.4653
5.750 0.9328 0.01769 0.00876 -0.0863 0.3197 0.4717
6.000 0.9567 0.01795 0.00901 -0.0855 0.3128 0.4781
6.250 0.9805 0.01819 0.00931 -0.0848 0.3064 0.4846
6.500 1.0045 0.01843 0.00961 -0.0841 0.2995 0.4921
6.750 1.0267 0.01874 0.00990 -0.0831 0.2930 0.4992
7.000 1.0500 0.01899 0.01024 -0.0823 0.2868 0.5062
7.250 1.0723 0.01928 0.01057 -0.0813 0.2802 0.5137
7.500 1.0922 0.01963 0.01091 -0.0800 0.2743 0.5208
7.750 1.1138 0.01989 0.01129 -0.0789 0.2683 0.5287
8.000 1.1332 0.02022 0.01164 -0.0775 0.2621 0.5375
8.500 1.1710 0.02096 0.01250 -0.0746 0.2508 0.5543
8.750 1.1893 0.02136 0.01296 -0.0731 0.2449 0.5626
9.000 1.2055 0.02187 0.01347 -0.0714 0.2397 0.5716
9.250 1.2250 0.02227 0.01398 -0.0702 0.2342 0.5815
9.500 1.2421 0.02275 0.01454 -0.0687 0.2286 0.5913
9.750 1.2567 0.02335 0.01514 -0.0669 0.2235 0.6016
10.000 1.2741 0.02384 0.01576 -0.0655 0.2185 0.6120
10.250 1.2898 0.02442 0.01642 -0.0640 0.2131 0.6231
10.500 1.3027 0.02512 0.01715 -0.0622 0.2083 0.6348
10.750 1.3172 0.02578 0.01792 -0.0606 0.2037 0.6467
11.000 1.3314 0.02648 0.01872 -0.0591 0.1987 0.6600
11.250 1.3427 0.02732 0.01963 -0.0574 0.1940 0.6732
11.500 1.3535 0.02824 0.02061 -0.0558 0.1899 0.6875
11.750 1.3664 0.02909 0.02160 -0.0544 0.1853 0.7036
12.000 1.3763 0.03012 0.02273 -0.0529 0.1808 0.7209
12.250 1.3831 0.03134 0.02400 -0.0512 0.1769 0.7402
12.500 1.3927 0.03243 0.02524 -0.0497 0.1731 0.7629
12.750 1.4004 0.03361 0.02658 -0.0482 0.1689 0.7914
13.250 1.3987 0.03624 0.02950 -0.0434 0.1623 1.0000
13.500 1.4079 0.03783 0.03116 -0.0429 0.1586 1.0000
13.750 1.4150 0.03961 0.03301 -0.0424 0.1546 1.0000
14.000 1.4192 0.04169 0.03511 -0.0420 0.1510 1.0000
14.250 1.4213 0.04403 0.03744 -0.0417 0.1479 1.0000
14.500 1.4280 0.04606 0.03959 -0.0415 0.1444 1.0000
14.750 1.4317 0.04843 0.04203 -0.0415 0.1409 1.0000
15.000 1.4327 0.05113 0.04477 -0.0417 0.1377 1.0000
15.250 1.4320 0.05407 0.04771 -0.0419 0.1348 1.0000
15.500 1.4355 0.05671 0.05047 -0.0423 0.1317 1.0000
15.750 1.4363 0.05970 0.05355 -0.0428 0.1286 1.0000
16.000 1.4348 0.06303 0.05693 -0.0435 0.1256 1.0000
16.250 1.4319 0.06659 0.06050 -0.0444 0.1230 1.0000
16.500 1.4324 0.06987 0.06390 -0.0452 0.1202 1.0000
16.750 1.4311 0.07347 0.06761 -0.0463 0.1174 1.0000
17.000 1.4280 0.07736 0.07155 -0.0476 0.1146 1.0000
17.250 1.4240 0.08140 0.07562 -0.0490 0.1122 1.0000
17.500 1.4216 0.08536 0.07967 -0.0505 0.1098 1.0000
17.750 1.4185 0.08951 0.08394 -0.0521 0.1072 1.0000
18.000 1.4143 0.09386 0.08837 -0.0539 0.1046 1.0000
18.250 1.4100 0.09822 0.09277 -0.0557 0.1023 1.0000
18.500 1.4069 0.10242 0.09701 -0.0575 0.1002 1.0000
18.750 1.4021 0.10707 0.10180 -0.0597 0.0978 1.0000
19.000 1.3967 0.11184 0.10667 -0.0620 0.0954 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S808 Airfoil (s808-nr)