NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S808 Airfoil (s808-nr) Reynolds number: 100,000 Max Cl/Cd: 36.55 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s808-nr-100000.txt Download as CSV file: xf-s808-nr-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2423 0.10409 0.09743 -0.0165 1.0000 0.3642
-8.250 -0.2277 0.10250 0.09587 -0.0154 1.0000 0.3680
-8.000 -0.3004 0.10469 0.09817 -0.0123 1.0000 0.3790
-7.750 -0.2678 0.10098 0.09446 -0.0118 1.0000 0.3800
-7.500 -0.2426 0.09848 0.09199 -0.0109 1.0000 0.3817
-7.250 -0.2259 0.09691 0.09047 -0.0094 1.0000 0.3845
-7.000 -0.2207 0.09597 0.08959 -0.0073 1.0000 0.3887
-6.750 -0.3114 0.09868 0.09247 -0.0009 1.0000 0.3983
-6.500 -0.2912 0.09633 0.09017 0.0007 1.0000 0.3993
-6.250 -0.2667 0.09436 0.08824 0.0007 0.9984 0.4008
-6.000 -0.2138 0.09145 0.08531 -0.0049 0.9923 0.4046
-5.750 -0.2270 0.09044 0.08424 -0.0124 0.9788 0.4178
-5.500 -0.1707 0.08643 0.08022 -0.0166 0.9716 0.4192
-5.250 -0.1148 0.08314 0.07691 -0.0219 0.9658 0.4217
-5.000 -0.0713 0.08064 0.07441 -0.0261 0.9554 0.4264
-4.750 -0.0834 0.07925 0.07299 -0.0306 0.9380 0.4381
-4.500 -0.0216 0.07547 0.06920 -0.0359 0.9336 0.4400
-4.250 0.0218 0.07281 0.06655 -0.0391 0.9211 0.4430
-4.000 0.0600 0.07041 0.06414 -0.0428 0.9096 0.4483
-3.750 -0.0656 0.05754 0.05093 -0.0533 0.8823 0.3976
-3.500 -0.0006 0.05997 0.05346 -0.0523 0.8719 0.4179
-3.250 0.0591 0.05721 0.05067 -0.0577 0.8657 0.4190
-3.000 0.1012 0.05445 0.04786 -0.0615 0.8520 0.4131
-2.750 0.1202 0.05138 0.04471 -0.0645 0.8365 0.4112
-2.500 0.1291 0.04780 0.04102 -0.0679 0.8203 0.4092
-2.250 0.1280 0.04324 0.03628 -0.0724 0.8042 0.4092
-2.000 0.1014 0.03426 0.02680 -0.0823 0.7869 0.4189
-1.750 0.1300 0.03440 0.02698 -0.0810 0.7705 0.4208
-1.500 0.1581 0.03420 0.02676 -0.0805 0.7551 0.4235
-1.250 0.1859 0.03309 0.02552 -0.0818 0.7410 0.4277
-1.000 0.2092 0.02982 0.02182 -0.0872 0.7268 0.4376
-0.750 0.2323 0.02994 0.02202 -0.0854 0.7116 0.4400
-0.500 0.2590 0.03003 0.02211 -0.0844 0.6979 0.4430
-0.250 0.2880 0.02965 0.02163 -0.0846 0.6851 0.4473
0.000 0.3119 0.02857 0.02041 -0.0860 0.6707 0.4536
0.250 0.3406 0.02777 0.01944 -0.0873 0.6582 0.4591
0.500 0.3662 0.02787 0.01956 -0.0862 0.6457 0.4625
0.750 0.3893 0.02789 0.01961 -0.0852 0.6327 0.4669
1.000 0.4225 0.02732 0.01881 -0.0870 0.6218 0.4741
1.250 0.4466 0.02689 0.01835 -0.0871 0.6085 0.4793
1.500 0.4724 0.02695 0.01842 -0.0863 0.5975 0.4830
1.750 0.4980 0.02695 0.01842 -0.0858 0.5859 0.4879
2.000 0.5263 0.02672 0.01808 -0.0866 0.5743 0.4955
2.250 0.5550 0.02656 0.01785 -0.0867 0.5639 0.5008
2.500 0.5770 0.02673 0.01812 -0.0855 0.5525 0.5053
2.750 0.6076 0.02665 0.01793 -0.0859 0.5428 0.5115
3.000 0.6339 0.02656 0.01781 -0.0864 0.5312 0.5191
3.250 0.6619 0.02664 0.01786 -0.0858 0.5223 0.5240
3.500 0.6828 0.02686 0.01820 -0.0847 0.5111 0.5301
3.750 0.7182 0.02675 0.01784 -0.0864 0.5021 0.5392
4.000 0.7367 0.02698 0.01829 -0.0846 0.4915 0.5436
4.250 0.7663 0.02706 0.01829 -0.0846 0.4829 0.5505
4.500 0.7913 0.02728 0.01853 -0.0847 0.4724 0.5597
4.750 0.8176 0.02738 0.01865 -0.0839 0.4641 0.5656
5.000 0.8396 0.02772 0.01910 -0.0830 0.4545 0.5733
5.250 0.8691 0.02780 0.01910 -0.0834 0.4457 0.5821
5.500 0.8913 0.02815 0.01956 -0.0822 0.4371 0.5888
5.750 0.9178 0.02837 0.01977 -0.0822 0.4280 0.5990
6.000 0.9441 0.02865 0.02005 -0.0816 0.4204 0.6068
6.250 0.9640 0.02904 0.02059 -0.0804 0.4111 0.6163
6.500 0.9964 0.02918 0.02058 -0.0809 0.4039 0.6258
6.750 1.0114 0.02974 0.02139 -0.0790 0.3949 0.6348
7.000 1.0392 0.02992 0.02153 -0.0789 0.3873 0.6453
7.250 1.0601 0.03046 0.02216 -0.0778 0.3795 0.6562
7.500 1.0802 0.03082 0.02264 -0.0765 0.3714 0.6665
7.750 1.1139 0.03113 0.02277 -0.0773 0.3645 0.6803
8.000 1.1224 0.03178 0.02376 -0.0743 0.3565 0.6893
8.250 1.1506 0.03198 0.02390 -0.0742 0.3493 0.7031
8.500 1.1686 0.03265 0.02470 -0.0727 0.3423 0.7160
8.750 1.1836 0.03317 0.02538 -0.0707 0.3348 0.7285
9.000 1.2177 0.03332 0.02535 -0.0713 0.3284 0.7447
9.250 1.2230 0.03430 0.02666 -0.0683 0.3212 0.7594
9.500 1.2414 0.03466 0.02708 -0.0667 0.3145 0.7758
9.750 1.2690 0.03501 0.02734 -0.0663 0.3084 0.7946
10.000 1.2682 0.03598 0.02864 -0.0624 0.3019 0.8121
10.250 1.2856 0.03624 0.02894 -0.0606 0.2958 0.8348
10.500 1.3066 0.03649 0.02914 -0.0589 0.2904 0.8620
10.750 1.2931 0.03738 0.03042 -0.0530 0.2852 0.8962
11.000 1.3055 0.03772 0.03089 -0.0512 0.2793 1.0000
11.250 1.3513 0.03846 0.03140 -0.0550 0.2722 1.0000
11.500 1.3480 0.04020 0.03338 -0.0525 0.2662 1.0000
11.750 1.3769 0.04077 0.03383 -0.0532 0.2599 1.0000
12.000 1.3987 0.04189 0.03489 -0.0532 0.2541 1.0000
12.250 1.3822 0.04395 0.03719 -0.0490 0.2495 1.0000
12.500 1.3940 0.04500 0.03824 -0.0477 0.2442 1.0000
12.750 0.7651 0.12661 0.12166 -0.0664 0.2300 1.0000
13.000 0.8075 0.12498 0.11994 -0.0660 0.2256 1.0000
13.250 0.8834 0.11654 0.11139 -0.0614 0.2235 1.0000
13.500 1.4371 0.05025 0.04350 -0.0431 0.2244 1.0000
13.750 1.4225 0.05322 0.04664 -0.0409 0.2208 1.0000
14.000 1.3602 0.05963 0.05346 -0.0381 0.2186 1.0000
14.750 1.3762 0.06610 0.05999 -0.0371 0.2057 1.0000
15.000 0.7848 0.18076 0.17588 -0.0936 0.2390 1.0000
15.250 0.7471 0.18285 0.17796 -0.0996 0.2307 1.0000
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Polar data table (+)
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