NREL's S816 Airfoil (s816-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S816 Airfoil (s816-nr) Reynolds number: 500,000 Max Cl/Cd: 96.92 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s816-nr-500000.txt Download as CSV file: xf-s816-nr-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.3781 0.15738 0.15500 -0.0502 1.0000 0.0130
-15.750 -0.3774 0.15254 0.15018 -0.0522 1.0000 0.0134
-10.000 -0.4244 0.03287 0.02669 -0.0949 0.7341 0.0095
-9.750 -0.3780 0.03297 0.02651 -0.0934 0.7249 0.0098
-9.500 -0.3538 0.03284 0.02620 -0.0922 0.7162 0.0102
-9.250 -0.3298 0.03283 0.02605 -0.0909 0.7084 0.0106
-8.750 -0.2945 0.03249 0.02565 -0.0881 0.6953 0.0118
-8.500 -0.2794 0.03190 0.02501 -0.0874 0.6897 0.0126
-8.250 -0.2651 0.03134 0.02436 -0.0864 0.6848 0.0136
-8.000 -0.2533 0.03066 0.02364 -0.0851 0.6800 0.0140
-7.750 -0.2477 0.02969 0.02263 -0.0835 0.6758 0.0142
-7.500 -0.2504 0.02819 0.02111 -0.0814 0.6719 0.0157
-7.250 -0.2449 0.02697 0.01986 -0.0801 0.6685 0.0175
-7.000 -0.2458 0.02535 0.01820 -0.0783 0.6649 0.0175
-6.750 -0.2526 0.02335 0.01616 -0.0762 0.6616 0.0198
-6.500 -0.2524 0.02175 0.01451 -0.0746 0.6586 0.0218
-6.250 -0.2535 0.02008 0.01274 -0.0728 0.6557 0.0245
-6.000 -0.2562 0.01834 0.01100 -0.0709 0.6528 0.0278
-5.750 -0.2522 0.01731 0.00991 -0.0690 0.6500 0.0309
-5.500 -0.2586 0.01586 0.00839 -0.0663 0.6475 0.0346
-5.250 -0.2437 0.01525 0.00770 -0.0654 0.6451 0.0411
-5.000 -0.2274 0.01462 0.00704 -0.0646 0.6430 0.0527
-4.750 -0.2092 0.01401 0.00645 -0.0642 0.6409 0.0780
-4.500 -0.1991 0.01247 0.00529 -0.0632 0.6391 0.2083
-4.250 -0.1862 0.01079 0.00427 -0.0628 0.6373 0.4258
-4.000 -0.1576 0.01087 0.00433 -0.0633 0.6354 0.4455
-3.750 -0.1287 0.01096 0.00438 -0.0639 0.6336 0.4552
-3.500 -0.0994 0.01110 0.00442 -0.0645 0.6319 0.4621
-3.250 -0.0705 0.01126 0.00456 -0.0650 0.6303 0.4699
-3.000 -0.0412 0.01144 0.00469 -0.0656 0.6288 0.4755
-2.750 -0.0118 0.01158 0.00471 -0.0663 0.6274 0.4786
-2.500 0.0172 0.01158 0.00469 -0.0670 0.6259 0.4818
-2.250 0.0462 0.01164 0.00474 -0.0676 0.6246 0.4843
-2.000 0.0750 0.01168 0.00479 -0.0681 0.6233 0.4869
-1.750 0.1039 0.01171 0.00479 -0.0687 0.6219 0.4891
-1.500 0.1329 0.01169 0.00474 -0.0694 0.6205 0.4904
-1.250 0.1619 0.01168 0.00470 -0.0700 0.6193 0.4915
-1.000 0.1910 0.01168 0.00467 -0.0707 0.6181 0.4926
-0.750 0.2203 0.01170 0.00465 -0.0714 0.6169 0.4936
-0.500 0.2492 0.01163 0.00458 -0.0721 0.6158 0.4951
-0.250 0.2782 0.01161 0.00457 -0.0727 0.6147 0.4966
0.000 0.3074 0.01163 0.00460 -0.0734 0.6138 0.4980
0.250 0.3367 0.01167 0.00464 -0.0742 0.6128 0.4995
0.500 0.3661 0.01174 0.00471 -0.0749 0.6119 0.5011
0.750 0.3956 0.01185 0.00481 -0.0757 0.6109 0.5028
1.000 0.4247 0.01194 0.00492 -0.0764 0.6100 0.5047
1.250 0.4534 0.01199 0.00499 -0.0770 0.6092 0.5066
1.500 0.4820 0.01205 0.00507 -0.0776 0.6081 0.5083
1.750 0.5105 0.01205 0.00513 -0.0782 0.6071 0.5103
2.000 0.5389 0.01209 0.00525 -0.0787 0.6062 0.5123
2.250 0.5675 0.01216 0.00538 -0.0793 0.6052 0.5142
2.500 0.5962 0.01225 0.00552 -0.0799 0.6043 0.5162
2.750 0.6249 0.01235 0.00567 -0.0806 0.6034 0.5184
3.000 0.6536 0.01245 0.00582 -0.0812 0.6025 0.5206
3.250 0.6824 0.01256 0.00596 -0.0819 0.6016 0.5227
3.500 0.7112 0.01263 0.00609 -0.0825 0.6005 0.5249
3.750 0.7398 0.01271 0.00626 -0.0831 0.5996 0.5273
4.000 0.7686 0.01283 0.00645 -0.0838 0.5988 0.5296
4.250 0.7977 0.01296 0.00664 -0.0844 0.5978 0.5321
4.500 0.8272 0.01311 0.00683 -0.0852 0.5965 0.5348
4.750 0.8560 0.01335 0.00711 -0.0859 0.5951 0.5373
5.000 0.8822 0.01336 0.00724 -0.0860 0.5930 0.5399
5.250 0.9081 0.01319 0.00720 -0.0859 0.5882 0.5425
5.500 0.9393 0.01290 0.00683 -0.0866 0.5804 0.5454
5.750 0.9608 0.01253 0.00659 -0.0855 0.5716 0.5482
6.000 0.9875 0.01233 0.00636 -0.0854 0.5636 0.5513
6.250 1.0111 0.01220 0.00633 -0.0848 0.5570 0.5543
6.500 1.0377 0.01210 0.00630 -0.0848 0.5517 0.5576
6.750 1.0606 0.01205 0.00639 -0.0842 0.5452 0.5609
7.000 1.0839 0.01195 0.00635 -0.0835 0.5370 0.5644
7.250 1.1049 0.01189 0.00641 -0.0825 0.5270 0.5679
7.500 1.1256 0.01183 0.00645 -0.0814 0.5148 0.5712
7.750 1.1437 0.01180 0.00653 -0.0797 0.4952 0.5746
8.000 1.1451 0.01206 0.00661 -0.0749 0.4387 0.5779
8.250 1.1220 0.01321 0.00739 -0.0661 0.3763 0.5806
8.750 1.0811 0.01656 0.01018 -0.0519 0.2647 0.5862
9.000 1.0648 0.01846 0.01190 -0.0466 0.2218 0.5891
9.250 1.0508 0.02058 0.01387 -0.0423 0.1846 0.5923
9.500 1.0392 0.02288 0.01601 -0.0389 0.1500 0.5958
9.750 1.0326 0.02508 0.01808 -0.0363 0.1231 0.5994
10.000 1.0284 0.02721 0.02014 -0.0342 0.1010 0.6032
10.250 1.0290 0.02909 0.02200 -0.0325 0.0848 0.6074
10.500 1.0311 0.03094 0.02381 -0.0311 0.0720 0.6121
10.750 1.0344 0.03273 0.02560 -0.0299 0.0616 0.6168
11.000 1.0377 0.03456 0.02744 -0.0287 0.0537 0.6214
11.250 1.0455 0.03609 0.02902 -0.0279 0.0480 0.6268
11.500 1.0473 0.03813 0.03105 -0.0268 0.0423 0.6319
11.750 1.0583 0.03947 0.03250 -0.0263 0.0390 0.6377
12.000 1.0645 0.04124 0.03428 -0.0256 0.0355 0.6438
12.250 1.0692 0.04317 0.03629 -0.0248 0.0325 0.6498
12.500 1.0792 0.04468 0.03790 -0.0244 0.0303 0.6566
12.750 1.0877 0.04637 0.03963 -0.0241 0.0279 0.6636
13.000 1.0884 0.04879 0.04213 -0.0233 0.0256 0.6702
13.250 1.1004 0.05022 0.04367 -0.0231 0.0241 0.6780
13.500 1.1105 0.05183 0.04537 -0.0229 0.0222 0.6863
13.750 1.1159 0.05394 0.04752 -0.0227 0.0204 0.6944
14.000 1.1233 0.05588 0.04957 -0.0225 0.0189 0.7038
14.250 1.1351 0.05741 0.05120 -0.0225 0.0174 0.7141
14.500 1.1440 0.05925 0.05309 -0.0226 0.0157 0.7247
14.750 1.1482 0.06162 0.05556 -0.0224 0.0146 0.7357
15.000 1.1590 0.06331 0.05740 -0.0225 0.0134 0.7485
15.250 1.1662 0.06543 0.05964 -0.0226 0.0126 0.7621
15.500 1.1706 0.06786 0.06215 -0.0227 0.0114 0.7773
16.000 1.1862 0.07195 0.06657 -0.0230 0.0096 0.8207
16.250 1.1909 0.07404 0.06885 -0.0227 0.0089 0.8611
16.500 1.1854 0.07697 0.07200 -0.0221 0.0082 1.0000
16.750 1.1913 0.07957 0.07470 -0.0226 0.0078 1.0000
17.000 1.1969 0.08224 0.07746 -0.0233 0.0071 1.0000
17.250 1.2013 0.08509 0.08038 -0.0240 0.0066 1.0000
17.500 1.2016 0.08854 0.08390 -0.0249 0.0062 1.0000
17.750 1.1973 0.09269 0.08815 -0.0259 0.0057 1.0000
18.000 1.1982 0.09620 0.09178 -0.0270 0.0055 1.0000
18.250 1.1978 0.09999 0.09569 -0.0282 0.0050 1.0000
18.500 1.1979 0.10373 0.09953 -0.0296 0.0049 1.0000
18.750 1.1970 0.10769 0.10358 -0.0311 0.0046 1.0000
19.000 1.1940 0.11205 0.10804 -0.0329 0.0045 1.0000
19.250 1.1887 0.11684 0.11293 -0.0350 0.0043 1.0000
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