NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S826 Airfoil (s826-nr) Reynolds number: 1,000,000 Max Cl/Cd: 137.7 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s826-nr-1000000.txt Download as CSV file: xf-s826-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S826 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2422 0.03897 0.03715 -0.1086 0.9746 0.0106
-9.000 -0.2502 0.03262 0.03066 -0.1161 0.9727 0.0106
-8.750 -0.2655 0.02883 0.02676 -0.1186 0.9657 0.0106
-8.500 -0.2673 0.02387 0.02161 -0.1271 0.9606 0.0108
-8.250 -0.2455 0.02030 0.01789 -0.1343 0.9592 0.0110
-7.250 -0.1958 0.01863 0.01459 -0.1467 0.9470 0.0080
-7.000 -0.1620 0.01604 0.01178 -0.1486 0.9462 0.0065
-6.750 -0.1478 0.01436 0.00993 -0.1463 0.9383 0.0061
-6.500 -0.1153 0.01285 0.00825 -0.1480 0.9354 0.0058
-6.250 -0.0791 0.01180 0.00711 -0.1504 0.9333 0.0057
-6.000 -0.0596 0.01108 0.00632 -0.1492 0.9231 0.0057
-5.750 -0.0210 0.01027 0.00543 -0.1520 0.9192 0.0058
-5.500 0.0118 0.00965 0.00474 -0.1535 0.9090 0.0060
-5.250 0.0593 0.00904 0.00404 -0.1581 0.9018 0.0064
-5.000 0.1065 0.00854 0.00343 -0.1625 0.8893 0.0073
-4.750 0.1480 0.00798 0.00280 -0.1658 0.8684 0.0219
-4.500 0.1801 0.00781 0.00253 -0.1669 0.8427 0.0349
-4.250 0.2086 0.00764 0.00232 -0.1674 0.8177 0.0610
-4.000 0.2364 0.00743 0.00215 -0.1677 0.7949 0.1075
-3.500 0.2956 0.00626 0.00160 -0.1701 0.7566 0.3900
-3.250 0.3224 0.00635 0.00161 -0.1699 0.7393 0.4068
-3.000 0.3492 0.00646 0.00161 -0.1697 0.7235 0.4157
-2.750 0.3762 0.00656 0.00164 -0.1696 0.7092 0.4257
-2.500 0.4034 0.00665 0.00164 -0.1694 0.6965 0.4319
-2.250 0.4306 0.00673 0.00166 -0.1693 0.6845 0.4364
-2.000 0.4580 0.00683 0.00168 -0.1693 0.6733 0.4415
-1.750 0.4857 0.00690 0.00168 -0.1693 0.6633 0.4458
-1.500 0.5132 0.00697 0.00171 -0.1693 0.6539 0.4495
-1.250 0.5409 0.00704 0.00173 -0.1693 0.6447 0.4525
-1.000 0.5686 0.00712 0.00176 -0.1693 0.6365 0.4560
-0.750 0.5962 0.00721 0.00178 -0.1693 0.6285 0.4581
-0.500 0.6242 0.00724 0.00179 -0.1694 0.6217 0.4604
-0.250 0.6520 0.00728 0.00182 -0.1695 0.6149 0.4627
0.000 0.6798 0.00735 0.00186 -0.1695 0.6091 0.4649
0.250 0.7079 0.00740 0.00190 -0.1696 0.6032 0.4672
0.500 0.7355 0.00749 0.00195 -0.1697 0.5976 0.4697
0.750 0.7636 0.00755 0.00200 -0.1698 0.5926 0.4720
1.000 0.7916 0.00761 0.00205 -0.1699 0.5877 0.4742
1.250 0.8192 0.00767 0.00212 -0.1699 0.5831 0.4770
1.500 0.8472 0.00773 0.00219 -0.1700 0.5784 0.4797
1.750 0.8749 0.00779 0.00226 -0.1701 0.5724 0.4826
2.000 0.9017 0.00791 0.00234 -0.1700 0.5656 0.4854
2.250 0.9294 0.00796 0.00241 -0.1700 0.5588 0.4880
2.750 0.9839 0.00809 0.00257 -0.1699 0.5455 0.4942
3.000 1.0110 0.00818 0.00267 -0.1698 0.5396 0.4973
3.250 1.0381 0.00827 0.00277 -0.1698 0.5338 0.5006
3.500 1.0652 0.00836 0.00286 -0.1697 0.5271 0.5036
3.750 1.0918 0.00846 0.00299 -0.1696 0.5211 0.5075
4.000 1.1193 0.00851 0.00310 -0.1696 0.5152 0.5112
4.250 1.1455 0.00863 0.00323 -0.1693 0.5081 0.5148
4.500 1.1723 0.00872 0.00334 -0.1692 0.5005 0.5182
4.750 1.1981 0.00885 0.00349 -0.1689 0.4913 0.5222
5.000 1.2245 0.00894 0.00363 -0.1687 0.4809 0.5262
5.250 1.2503 0.00908 0.00378 -0.1684 0.4694 0.5303
5.500 1.2750 0.00926 0.00394 -0.1679 0.4523 0.5342
5.750 1.2983 0.00953 0.00415 -0.1671 0.4235 0.5389
6.000 1.3171 0.01013 0.00451 -0.1656 0.3703 0.5434
6.250 1.3327 0.01100 0.00506 -0.1636 0.3100 0.5476
6.500 1.3482 0.01185 0.00565 -0.1616 0.2552 0.5519
6.750 1.3643 0.01261 0.00620 -0.1596 0.2111 0.5566
7.000 1.3792 0.01337 0.00675 -0.1575 0.1728 0.5614
7.250 1.3918 0.01410 0.00731 -0.1549 0.1369 0.5660
7.500 1.4046 0.01481 0.00788 -0.1523 0.1086 0.5712
7.750 1.4188 0.01546 0.00843 -0.1500 0.0883 0.5768
8.000 1.4336 0.01606 0.00899 -0.1479 0.0727 0.5826
8.250 1.4489 0.01665 0.00955 -0.1458 0.0609 0.5891
8.500 1.4635 0.01726 0.01013 -0.1437 0.0505 0.5958
8.750 1.4779 0.01789 0.01076 -0.1416 0.0420 0.6036
9.000 1.4917 0.01857 0.01143 -0.1395 0.0346 0.6118
9.250 1.5064 0.01919 0.01208 -0.1375 0.0295 0.6213
9.500 1.5199 0.01990 0.01283 -0.1354 0.0244 0.6313
9.750 1.5319 0.02071 0.01365 -0.1331 0.0194 0.6423
10.000 1.5433 0.02157 0.01454 -0.1308 0.0151 0.6548
10.250 1.5536 0.02251 0.01553 -0.1285 0.0112 0.6692
10.500 1.5630 0.02357 0.01664 -0.1261 0.0079 0.6859
10.750 1.5706 0.02478 0.01793 -0.1235 0.0052 0.7060
11.000 1.5757 0.02622 0.01948 -0.1208 0.0034 0.7304
11.250 1.5819 0.02761 0.02103 -0.1183 0.0026 0.7655
11.500 1.5855 0.02925 0.02292 -0.1158 0.0022 0.8291
11.750 1.5889 0.03033 0.02428 -0.1129 0.0020 1.0000
12.000 1.5955 0.03193 0.02597 -0.1110 0.0019 1.0000
12.250 1.6012 0.03366 0.02779 -0.1092 0.0018 1.0000
12.500 1.6063 0.03553 0.02974 -0.1075 0.0017 1.0000
12.750 1.6109 0.03753 0.03183 -0.1060 0.0017 1.0000
13.000 1.6145 0.03970 0.03409 -0.1046 0.0016 1.0000
13.250 1.6173 0.04203 0.03652 -0.1033 0.0015 1.0000
13.500 1.6194 0.04455 0.03914 -0.1022 0.0015 1.0000
13.750 1.6204 0.04730 0.04199 -0.1012 0.0015 1.0000
14.000 1.6203 0.05025 0.04505 -0.1004 0.0014 1.0000
14.250 1.6189 0.05348 0.04840 -0.0998 0.0014 1.0000
14.500 1.6166 0.05694 0.05197 -0.0993 0.0014 1.0000
14.750 1.6129 0.06070 0.05586 -0.0991 0.0014 1.0000
15.000 1.6095 0.06452 0.05979 -0.0990 0.0014 1.0000
15.250 1.6033 0.06887 0.06428 -0.0992 0.0013 1.0000
15.500 1.5972 0.07335 0.06889 -0.0997 0.0013 1.0000
15.750 1.5902 0.07810 0.07377 -0.1003 0.0013 1.0000
16.000 1.5826 0.08306 0.07886 -0.1012 0.0013 1.0000
16.250 1.5737 0.08839 0.08433 -0.1024 0.0013 1.0000
16.500 1.5653 0.09379 0.08986 -0.1038 0.0013 1.0000
16.750 1.5548 0.09964 0.09586 -0.1056 0.0013 1.0000
17.000 1.5465 0.10526 0.10160 -0.1074 0.0013 1.0000
17.250 1.5377 0.11109 0.10757 -0.1096 0.0013 1.0000
17.500 1.5262 0.11757 0.11419 -0.1122 0.0013 1.0000
17.750 1.5168 0.12376 0.12050 -0.1150 0.0013 1.0000
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