NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S826 Airfoil (s826-nr) Reynolds number: 500,000 Max Cl/Cd: 107.67 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s826-nr-500000-n5.txt Download as CSV file: xf-s826-nr-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2949 0.11023 0.10781 -0.0645 0.9879 0.0073
-11.000 -0.2849 0.10625 0.10382 -0.0679 0.9866 0.0070
-10.750 -0.2753 0.10158 0.09916 -0.0719 0.9854 0.0067
-10.500 -0.2682 0.09615 0.09373 -0.0763 0.9844 0.0064
-10.000 -0.2935 0.07676 0.07439 -0.0864 0.9794 0.0051
-9.750 -0.3093 0.06600 0.06362 -0.0949 0.9763 0.0050
-9.500 -0.3218 0.05724 0.05475 -0.1038 0.9735 0.0049
-9.250 -0.3395 0.05004 0.04740 -0.1100 0.9684 0.0048
-9.000 -0.3521 0.04499 0.04221 -0.1139 0.9611 0.0048
-8.750 -0.3633 0.03949 0.03649 -0.1183 0.9516 0.0047
-8.500 -0.3560 0.03140 0.02784 -0.1270 0.9459 0.0045
-8.250 -0.3535 0.02714 0.02316 -0.1271 0.9359 0.0044
-8.000 -0.3286 0.02330 0.01885 -0.1299 0.9326 0.0043
-7.750 -0.3153 0.02117 0.01643 -0.1287 0.9230 0.0043
-7.500 -0.2872 0.01931 0.01430 -0.1300 0.9192 0.0043
-7.250 -0.2679 0.01806 0.01289 -0.1293 0.9097 0.0044
-6.750 -0.2083 0.01571 0.01025 -0.1317 0.8972 0.0045
-6.500 -0.1705 0.01459 0.00901 -0.1346 0.8922 0.0046
-6.250 -0.1311 0.01364 0.00793 -0.1378 0.8846 0.0047
-6.000 -0.0829 0.01270 0.00686 -0.1428 0.8784 0.0050
-5.750 -0.0315 0.01187 0.00590 -0.1486 0.8694 0.0054
-5.500 0.0163 0.01126 0.00515 -0.1534 0.8565 0.0062
-5.250 0.0573 0.01081 0.00455 -0.1566 0.8384 0.0081
-5.000 0.0920 0.01049 0.00410 -0.1585 0.8185 0.0127
-4.750 0.1226 0.01028 0.00378 -0.1594 0.7985 0.0185
-4.500 0.1520 0.01004 0.00349 -0.1601 0.7795 0.0319
-4.250 0.1811 0.00976 0.00321 -0.1609 0.7617 0.0598
-4.000 0.2096 0.00953 0.00297 -0.1614 0.7453 0.0925
-3.500 0.2721 0.00821 0.00224 -0.1648 0.7172 0.3597
-3.250 0.3000 0.00824 0.00224 -0.1649 0.7049 0.3927
-3.000 0.3277 0.00832 0.00224 -0.1649 0.6937 0.4102
-2.750 0.3552 0.00839 0.00222 -0.1649 0.6833 0.4184
-2.500 0.3828 0.00847 0.00221 -0.1649 0.6732 0.4262
-2.250 0.4105 0.00854 0.00222 -0.1649 0.6637 0.4332
-2.000 0.4379 0.00863 0.00223 -0.1648 0.6548 0.4391
-1.750 0.4658 0.00870 0.00221 -0.1649 0.6461 0.4434
-1.500 0.4934 0.00876 0.00222 -0.1649 0.6386 0.4469
-1.250 0.5213 0.00880 0.00223 -0.1650 0.6314 0.4493
-1.000 0.5490 0.00887 0.00224 -0.1650 0.6250 0.4514
-0.750 0.5770 0.00892 0.00225 -0.1651 0.6186 0.4537
-0.500 0.6047 0.00899 0.00226 -0.1651 0.6126 0.4561
-0.250 0.6326 0.00905 0.00229 -0.1652 0.6069 0.4584
0.000 0.6604 0.00910 0.00233 -0.1653 0.6010 0.4604
0.250 0.6880 0.00918 0.00238 -0.1653 0.5959 0.4625
0.500 0.7161 0.00923 0.00244 -0.1654 0.5912 0.4648
0.750 0.7440 0.00930 0.00250 -0.1655 0.5865 0.4674
1.000 0.7716 0.00939 0.00257 -0.1655 0.5822 0.4702
1.250 0.7995 0.00946 0.00265 -0.1656 0.5780 0.4729
1.500 0.8273 0.00952 0.00273 -0.1657 0.5735 0.4752
1.750 0.8550 0.00961 0.00282 -0.1658 0.5695 0.4777
2.000 0.8825 0.00971 0.00293 -0.1658 0.5659 0.4803
2.250 0.9103 0.00977 0.00304 -0.1659 0.5614 0.4832
2.500 0.9373 0.00987 0.00315 -0.1658 0.5554 0.4864
2.750 0.9640 0.00998 0.00326 -0.1656 0.5483 0.4894
3.000 0.9903 0.01008 0.00339 -0.1654 0.5397 0.4923
3.250 1.0166 0.01018 0.00351 -0.1652 0.5309 0.4953
3.500 1.0425 0.01032 0.00364 -0.1649 0.5225 0.4985
3.750 1.0691 0.01042 0.00378 -0.1647 0.5150 0.5017
4.000 1.0946 0.01057 0.00394 -0.1643 0.5066 0.5048
4.250 1.1208 0.01067 0.00410 -0.1641 0.4973 0.5079
4.500 1.1464 0.01081 0.00428 -0.1638 0.4885 0.5117
4.750 1.1713 0.01097 0.00446 -0.1633 0.4778 0.5157
5.000 1.1962 0.01113 0.00465 -0.1628 0.4644 0.5195
5.250 1.2199 0.01133 0.00486 -0.1621 0.4461 0.5231
5.500 1.2413 0.01164 0.00510 -0.1610 0.4144 0.5270
5.750 1.2572 0.01230 0.00552 -0.1589 0.3602 0.5308
6.000 1.2720 0.01312 0.00608 -0.1567 0.3082 0.5344
6.250 1.2868 0.01395 0.00669 -0.1546 0.2607 0.5381
6.500 1.3015 0.01468 0.00726 -0.1524 0.2222 0.5422
6.750 1.3156 0.01538 0.00782 -0.1502 0.1899 0.5465
7.000 1.3311 0.01602 0.00839 -0.1481 0.1651 0.5506
7.250 1.3458 0.01669 0.00898 -0.1460 0.1421 0.5553
7.500 1.3602 0.01737 0.00959 -0.1439 0.1210 0.5606
7.750 1.3745 0.01806 0.01023 -0.1417 0.1038 0.5657
8.000 1.3887 0.01873 0.01089 -0.1396 0.0890 0.5713
8.250 1.4021 0.01947 0.01161 -0.1374 0.0744 0.5771
8.500 1.4148 0.02025 0.01237 -0.1352 0.0616 0.5827
8.750 1.4274 0.02104 0.01316 -0.1330 0.0518 0.5890
9.000 1.4396 0.02187 0.01400 -0.1308 0.0438 0.5953
9.250 1.4522 0.02269 0.01485 -0.1287 0.0371 0.6024
9.500 1.4635 0.02360 0.01580 -0.1265 0.0306 0.6098
9.750 1.4733 0.02464 0.01685 -0.1242 0.0241 0.6181
10.000 1.4822 0.02577 0.01801 -0.1219 0.0186 0.6271
10.250 1.4907 0.02696 0.01925 -0.1196 0.0141 0.6374
10.500 1.4990 0.02821 0.02057 -0.1175 0.0109 0.6484
10.750 1.5082 0.02945 0.02190 -0.1156 0.0089 0.6607
11.000 1.5162 0.03084 0.02338 -0.1137 0.0073 0.6743
11.250 1.5239 0.03231 0.02496 -0.1119 0.0060 0.6899
11.500 1.5311 0.03389 0.02667 -0.1102 0.0051 0.7086
11.750 1.5381 0.03554 0.02846 -0.1086 0.0043 0.7324
12.000 1.5431 0.03744 0.03054 -0.1071 0.0036 0.7654
12.250 1.5497 0.03918 0.03253 -0.1057 0.0032 0.8271
12.500 1.5491 0.04085 0.03443 -0.1032 0.0028 1.0000
12.750 1.5531 0.04309 0.03675 -0.1020 0.0025 1.0000
13.000 1.5550 0.04565 0.03941 -0.1009 0.0022 1.0000
13.250 1.5592 0.04804 0.04192 -0.1001 0.0021 1.0000
13.500 1.5624 0.05062 0.04461 -0.0994 0.0019 1.0000
13.750 1.5648 0.05336 0.04747 -0.0988 0.0017 1.0000
14.000 1.5668 0.05623 0.05046 -0.0983 0.0016 1.0000
14.250 1.5681 0.05928 0.05362 -0.0980 0.0015 1.0000
14.500 1.5686 0.06249 0.05695 -0.0978 0.0015 1.0000
14.750 1.5677 0.06598 0.06057 -0.0978 0.0014 1.0000
15.000 1.5664 0.06963 0.06435 -0.0979 0.0013 1.0000
15.250 1.5623 0.07377 0.06863 -0.0983 0.0013 1.0000
15.500 1.5572 0.07820 0.07320 -0.0988 0.0012 1.0000
15.750 1.5503 0.08301 0.07816 -0.0997 0.0012 1.0000
16.000 1.5460 0.08753 0.08282 -0.1006 0.0012 1.0000
16.250 1.5407 0.09232 0.08776 -0.1018 0.0012 1.0000
16.500 1.5345 0.09736 0.09294 -0.1032 0.0012 1.0000
16.750 1.5270 0.10272 0.09845 -0.1049 0.0011 1.0000
17.000 1.5195 0.10822 0.10410 -0.1069 0.0011 1.0000
17.250 1.5111 0.11402 0.11005 -0.1091 0.0011 1.0000
17.500 1.5018 0.12011 0.11629 -0.1117 0.0011 1.0000
17.750 1.4922 0.12638 0.12271 -0.1146 0.0011 1.0000
18.000 1.4819 0.13294 0.12943 -0.1179 0.0011 1.0000
18.250 1.4715 0.13970 0.13633 -0.1215 0.0011 1.0000
18.500 1.4603 0.14678 0.14356 -0.1255 0.0011 1.0000
18.750 1.4501 0.15378 0.15070 -0.1297 0.0011 1.0000
19.000 1.4394 0.16100 0.15807 -0.1342 0.0011 1.0000
19.250 1.4277 0.16862 0.16583 -0.1391 0.0011 1.0000
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