NREL's S816 Airfoil (s816-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S816 Airfoil (s816-nr) Reynolds number: 200,000 Max Cl/Cd: 59.02 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s816-nr-200000.txt Download as CSV file: xf-s816-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S816 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4795 0.09400 0.09052 -0.0758 1.0000 0.0381
-12.250 -0.5033 0.09026 0.08675 -0.0756 1.0000 0.0381
-12.000 -0.5249 0.08698 0.08348 -0.0749 0.9997 0.0380
-11.750 -0.5474 0.08193 0.07812 -0.0814 0.9896 0.0389
-11.500 -0.5589 0.07788 0.07381 -0.0864 0.9775 0.0391
-11.000 -0.5808 0.07266 0.06798 -0.0914 0.9241 0.0396
-10.750 -0.5539 0.06184 0.05721 -0.0963 0.9144 0.0412
-10.500 -0.5360 0.05785 0.05307 -0.0988 0.8883 0.0424
-10.250 -0.5316 0.05521 0.05016 -0.0986 0.8608 0.0438
-10.000 -0.5317 0.05329 0.04793 -0.0967 0.8395 0.0457
-9.750 -0.5341 0.05265 0.04692 -0.0936 0.8220 0.0484
-9.500 -0.5506 0.05623 0.04990 -0.0877 0.8065 0.0501
-9.250 -0.5318 0.04740 0.04111 -0.0895 0.7979 0.0527
-9.000 -0.5160 0.04502 0.03863 -0.0891 0.7889 0.0547
-8.500 -0.3045 0.01994 0.01265 -0.0916 0.7669 0.0287
-8.250 -0.4308 0.03563 0.02819 -0.0872 0.7677 0.0423
-8.000 -0.2117 0.03397 0.02598 -0.0937 0.7676 0.0316
-7.750 -0.1910 0.03389 0.02592 -0.0925 0.7618 0.0349
-7.500 -0.1736 0.03350 0.02545 -0.0914 0.7552 0.0396
-7.250 -0.1605 0.03327 0.02531 -0.0893 0.7501 0.0457
-7.000 -0.1501 0.03269 0.02468 -0.0877 0.7454 0.0515
-6.750 -0.1461 0.03164 0.02369 -0.0861 0.7404 0.0573
-6.500 -0.1433 0.03044 0.02243 -0.0844 0.7361 0.0639
-6.250 -0.1493 0.02875 0.02075 -0.0823 0.7326 0.0697
-6.000 -0.1531 0.02701 0.01896 -0.0805 0.7287 0.0768
-5.750 -0.1703 0.02437 0.01628 -0.0780 0.7246 0.0808
-5.500 -0.1845 0.02212 0.01392 -0.0754 0.7209 0.0875
-5.250 -0.2012 0.02042 0.01207 -0.0719 0.7177 0.0952
-5.000 -0.2094 0.01883 0.01047 -0.0689 0.7145 0.1280
-4.750 -0.2276 0.01625 0.00886 -0.0652 0.7113 0.4354
-4.500 -0.2010 0.01755 0.01012 -0.0648 0.7085 0.4767
-4.250 -0.1728 0.01869 0.01117 -0.0645 0.7061 0.4936
-4.000 -0.1381 0.02040 0.01305 -0.0643 0.7040 0.5055
-3.750 -0.1006 0.02235 0.01511 -0.0642 0.7022 0.5145
-3.500 -0.0721 0.02306 0.01577 -0.0642 0.7003 0.5206
-3.250 -0.0501 0.02287 0.01549 -0.0641 0.6980 0.5251
-3.000 -0.0083 0.02524 0.01808 -0.0637 0.6960 0.5286
-2.750 0.0183 0.02546 0.01826 -0.0637 0.6939 0.5308
-2.500 0.0376 0.02455 0.01723 -0.0640 0.6918 0.5323
-2.250 0.0586 0.02366 0.01619 -0.0646 0.6900 0.5335
-2.000 0.0817 0.02296 0.01535 -0.0653 0.6884 0.5347
-1.750 0.1061 0.02241 0.01464 -0.0661 0.6871 0.5361
-1.500 0.1305 0.02199 0.01409 -0.0668 0.6857 0.5376
-1.250 0.1537 0.02171 0.01374 -0.0672 0.6840 0.5388
-1.000 0.1781 0.02163 0.01368 -0.0674 0.6824 0.5397
-0.750 0.2030 0.02163 0.01370 -0.0676 0.6808 0.5406
-0.500 0.2282 0.02166 0.01375 -0.0678 0.6793 0.5416
-0.250 0.2538 0.02171 0.01380 -0.0681 0.6777 0.5428
0.000 0.2798 0.02174 0.01382 -0.0685 0.6761 0.5442
0.250 0.3063 0.02177 0.01385 -0.0689 0.6747 0.5457
0.500 0.3329 0.02184 0.01391 -0.0694 0.6735 0.5476
0.750 0.3598 0.02191 0.01395 -0.0701 0.6725 0.5498
1.000 0.3871 0.02200 0.01398 -0.0709 0.6715 0.5523
1.250 0.4112 0.02221 0.01421 -0.0711 0.6704 0.5543
1.500 0.4294 0.02264 0.01476 -0.0703 0.6686 0.5557
1.750 0.4480 0.02309 0.01533 -0.0696 0.6663 0.5572
2.000 0.4675 0.02358 0.01591 -0.0690 0.6645 0.5590
2.250 0.4877 0.02407 0.01647 -0.0686 0.6629 0.5610
2.500 0.5108 0.02441 0.01684 -0.0686 0.6611 0.5634
2.750 0.5360 0.02468 0.01712 -0.0690 0.6596 0.5661
3.000 0.5629 0.02494 0.01736 -0.0697 0.6584 0.5688
3.250 0.5911 0.02508 0.01760 -0.0702 0.6572 0.5708
3.500 0.6192 0.02535 0.01795 -0.0708 0.6561 0.5729
3.750 0.5759 0.02862 0.02145 -0.0620 0.6482 0.5742
4.000 0.5910 0.02937 0.02227 -0.0609 0.6454 0.5766
4.250 0.6179 0.02965 0.02261 -0.0614 0.6437 0.5796
4.500 0.6508 0.02971 0.02268 -0.0628 0.6426 0.5831
4.750 0.6865 0.02959 0.02266 -0.0643 0.6417 0.5859
5.000 0.7229 0.02953 0.02272 -0.0659 0.6409 0.5889
5.250 0.5401 0.03997 0.03311 -0.0427 0.6140 0.5874
5.500 0.5778 0.03955 0.03281 -0.0439 0.6127 0.5906
5.750 0.6194 0.03892 0.03229 -0.0455 0.6119 0.5946
6.000 0.6631 0.03817 0.03158 -0.0474 0.6114 0.5992
6.250 0.7089 0.03708 0.03068 -0.0493 0.6110 0.6025
6.500 0.7525 0.03627 0.03003 -0.0511 0.6099 0.6062
6.750 0.8285 0.03377 0.02767 -0.0569 0.6098 0.6117
7.000 0.9872 0.02482 0.01875 -0.0713 0.5978 0.6188
7.250 1.0125 0.02433 0.01841 -0.0707 0.5902 0.6229
7.500 1.0665 0.02247 0.01653 -0.0741 0.5817 0.6291
7.750 1.0806 0.02228 0.01654 -0.0717 0.5726 0.6327
8.000 1.1147 0.02112 0.01549 -0.0721 0.5620 0.6375
8.250 1.1418 0.02018 0.01460 -0.0714 0.5491 0.6432
8.500 1.1528 0.01965 0.01423 -0.0682 0.5342 0.6475
8.750 1.1520 0.01952 0.01429 -0.0631 0.5176 0.6515
9.000 1.1435 0.01969 0.01462 -0.0570 0.4964 0.6562
9.250 1.1382 0.01980 0.01461 -0.0516 0.4390 0.6614
9.500 1.1131 0.02113 0.01542 -0.0441 0.3685 0.6650
9.750 1.0841 0.02363 0.01761 -0.0378 0.3185 0.6692
10.000 1.0559 0.02675 0.02045 -0.0329 0.2713 0.6738
10.250 1.0308 0.03012 0.02358 -0.0291 0.2269 0.6778
10.500 1.0085 0.03358 0.02680 -0.0260 0.1843 0.6817
10.750 0.9921 0.03683 0.02983 -0.0236 0.1479 0.6868
11.000 0.9821 0.03975 0.03256 -0.0219 0.1217 0.6922
11.250 0.9758 0.04240 0.03512 -0.0203 0.1040 0.6970
11.500 0.9733 0.04489 0.03755 -0.0191 0.0905 0.7036
11.750 0.9761 0.04695 0.03966 -0.0182 0.0800 0.7098
12.000 0.9792 0.04904 0.04178 -0.0173 0.0722 0.7170
12.250 0.9832 0.05106 0.04379 -0.0165 0.0655 0.7245
12.500 0.9917 0.05273 0.04556 -0.0158 0.0597 0.7330
12.750 0.9996 0.05445 0.04734 -0.0153 0.0550 0.7415
13.000 1.0098 0.05600 0.04894 -0.0145 0.0505 0.7517
13.250 1.0199 0.05756 0.05064 -0.0140 0.0464 0.7616
13.500 1.0341 0.05867 0.05171 -0.0130 0.0422 0.7725
13.750 1.0443 0.06035 0.05363 -0.0127 0.0395 0.7854
14.000 1.0558 0.06187 0.05529 -0.0123 0.0367 0.7997
14.250 1.0760 0.06266 0.05606 -0.0111 0.0332 0.8160
14.500 1.0820 0.06460 0.05829 -0.0106 0.0313 0.8362
14.750 1.0887 0.06627 0.06019 -0.0096 0.0293 0.8651
15.000 1.0904 0.06731 0.06145 -0.0076 0.0277 1.0000
15.250 1.1081 0.06922 0.06336 -0.0077 0.0253 1.0000
15.500 1.1108 0.07216 0.06651 -0.0083 0.0237 1.0000
15.750 1.1169 0.07487 0.06938 -0.0087 0.0223 1.0000
16.000 1.1220 0.07753 0.07209 -0.0094 0.0210 1.0000
16.250 1.1305 0.08050 0.07510 -0.0094 0.0195 1.0000
16.500 1.1219 0.08463 0.07951 -0.0105 0.0186 1.0000
16.750 1.1182 0.08882 0.08397 -0.0112 0.0180 1.0000
17.000 1.1143 0.09278 0.08810 -0.0124 0.0171 1.0000
17.250 1.1121 0.09655 0.09198 -0.0137 0.0164 1.0000
17.500 1.1080 0.10075 0.09631 -0.0151 0.0159 1.0000
17.750 1.1050 0.10486 0.10051 -0.0166 0.0154 1.0000
18.000 1.0963 0.11005 0.10586 -0.0183 0.0151 1.0000
18.250 1.0772 0.11713 0.11318 -0.0210 0.0149 1.0000
18.500 1.0618 0.12371 0.11998 -0.0242 0.0149 1.0000
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