NREL's S831 Airfoil (s831-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S831 Airfoil (s831-nr) Reynolds number: 1,000,000 Max Cl/Cd: 147.47 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s831-nr-1000000-n5.txt Download as CSV file: xf-s831-nr-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S831 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 0.1113 0.09292 0.08991 -0.1528 0.7477 0.0058
-12.500 0.1143 0.08944 0.08643 -0.1541 0.7458 0.0059
-12.250 0.1178 0.08623 0.08321 -0.1552 0.7436 0.0059
-12.000 0.1254 0.08408 0.08106 -0.1561 0.7413 0.0061
-11.750 0.1302 0.08129 0.07826 -0.1571 0.7390 0.0063
-11.500 0.1326 0.07784 0.07480 -0.1584 0.7370 0.0063
-11.000 0.1382 0.07136 0.06831 -0.1607 0.7332 0.0068
-10.750 0.1374 0.06733 0.06429 -0.1620 0.7314 0.0066
-10.500 0.1393 0.06399 0.06096 -0.1632 0.7294 0.0071
-10.250 0.1376 0.05991 0.05689 -0.1647 0.7274 0.0070
-10.000 0.1345 0.05569 0.05267 -0.1663 0.7253 0.0069
-9.750 0.1307 0.05138 0.04836 -0.1682 0.7233 0.0075
-9.500 0.1227 0.04643 0.04342 -0.1710 0.7211 0.0072
-7.000 -0.0129 0.01864 0.01350 -0.1632 0.7043 0.0036
-6.750 0.0053 0.01643 0.01097 -0.1620 0.7026 0.0035
-6.500 0.0267 0.01515 0.00948 -0.1613 0.7009 0.0035
-6.250 0.0490 0.01423 0.00840 -0.1607 0.6991 0.0035
-6.000 0.0712 0.01346 0.00750 -0.1601 0.6972 0.0035
-5.750 0.0934 0.01283 0.00677 -0.1595 0.6954 0.0035
-5.500 0.1160 0.01233 0.00618 -0.1590 0.6935 0.0035
-5.000 0.1625 0.01142 0.00514 -0.1584 0.6905 0.0035
-4.750 0.1872 0.01104 0.00471 -0.1583 0.6891 0.0035
-4.500 0.2124 0.01072 0.00435 -0.1583 0.6877 0.0036
-4.250 0.2381 0.01043 0.00401 -0.1585 0.6862 0.0036
-4.000 0.2642 0.01018 0.00373 -0.1586 0.6847 0.0036
-3.750 0.2905 0.00994 0.00344 -0.1589 0.6832 0.0038
-3.500 0.3171 0.00974 0.00320 -0.1591 0.6817 0.0039
-3.250 0.3439 0.00956 0.00298 -0.1594 0.6803 0.0046
-3.000 0.3708 0.00942 0.00282 -0.1597 0.6789 0.0060
-2.500 0.4255 0.00914 0.00260 -0.1605 0.6762 0.0233
-2.250 0.4532 0.00903 0.00252 -0.1610 0.6749 0.0309
-2.000 0.4810 0.00893 0.00246 -0.1615 0.6736 0.0423
-1.750 0.5088 0.00875 0.00239 -0.1621 0.6723 0.0796
-1.500 0.5400 0.00703 0.00208 -0.1652 0.6711 0.5827
-1.250 0.5682 0.00704 0.00209 -0.1656 0.6698 0.6044
-1.000 0.5963 0.00706 0.00211 -0.1661 0.6685 0.6177
-0.750 0.6242 0.00709 0.00213 -0.1665 0.6673 0.6249
-0.500 0.6521 0.00714 0.00216 -0.1669 0.6661 0.6347
-0.250 0.6798 0.00718 0.00219 -0.1672 0.6648 0.6395
0.000 0.7078 0.00724 0.00222 -0.1676 0.6636 0.6447
0.250 0.7358 0.00730 0.00225 -0.1681 0.6624 0.6471
0.500 0.7635 0.00733 0.00227 -0.1685 0.6614 0.6487
0.750 0.7909 0.00735 0.00231 -0.1688 0.6602 0.6506
1.000 0.8183 0.00739 0.00235 -0.1692 0.6589 0.6526
1.250 0.8457 0.00742 0.00240 -0.1695 0.6578 0.6546
1.500 0.8729 0.00747 0.00246 -0.1698 0.6566 0.6566
1.750 0.9001 0.00751 0.00251 -0.1701 0.6554 0.6586
2.000 0.9270 0.00757 0.00257 -0.1704 0.6542 0.6606
2.250 0.9536 0.00762 0.00263 -0.1705 0.6531 0.6625
2.750 1.0063 0.00774 0.00277 -0.1708 0.6506 0.6662
3.000 1.0331 0.00781 0.00285 -0.1711 0.6493 0.6682
3.250 1.0599 0.00788 0.00294 -0.1713 0.6481 0.6705
3.500 1.0852 0.00793 0.00304 -0.1713 0.6471 0.6729
3.750 1.1108 0.00799 0.00314 -0.1713 0.6461 0.6753
4.000 1.1362 0.00806 0.00324 -0.1713 0.6449 0.6775
4.250 1.1615 0.00813 0.00336 -0.1712 0.6437 0.6795
4.500 1.1866 0.00820 0.00348 -0.1711 0.6423 0.6816
4.750 1.2116 0.00828 0.00361 -0.1710 0.6409 0.6838
5.000 1.2343 0.00837 0.00374 -0.1704 0.6382 0.6862
5.250 1.2502 0.00849 0.00387 -0.1684 0.6314 0.6887
5.500 1.2616 0.00865 0.00403 -0.1654 0.6207 0.6914
5.750 1.2741 0.00886 0.00424 -0.1627 0.6082 0.6940
6.000 1.2892 0.00909 0.00448 -0.1606 0.5965 0.6965
6.250 1.3042 0.00935 0.00476 -0.1586 0.5855 0.6992
6.500 1.3183 0.00967 0.00508 -0.1564 0.5728 0.7020
6.750 1.3290 0.01010 0.00549 -0.1537 0.5564 0.7048
7.000 1.3302 0.01084 0.00614 -0.1492 0.5297 0.7076
7.250 1.3171 0.01217 0.00728 -0.1424 0.4892 0.7103
7.500 1.2971 0.01398 0.00889 -0.1348 0.4443 0.7132
7.750 1.2828 0.01582 0.01056 -0.1286 0.4057 0.7165
8.000 1.2691 0.01783 0.01240 -0.1229 0.3652 0.7199
8.250 1.2551 0.02005 0.01443 -0.1175 0.3239 0.7230
8.500 1.2524 0.02178 0.01605 -0.1140 0.2954 0.7258
8.750 1.2455 0.02384 0.01796 -0.1100 0.2599 0.7286
9.000 1.2422 0.02579 0.01977 -0.1067 0.2285 0.7315
9.250 1.2423 0.02759 0.02146 -0.1040 0.2007 0.7346
9.500 1.2444 0.02931 0.02307 -0.1015 0.1742 0.7379
10.000 1.2485 0.03292 0.02646 -0.0970 0.1220 0.7438
10.250 1.2555 0.03443 0.02791 -0.0954 0.1053 0.7472
10.500 1.2629 0.03594 0.02936 -0.0939 0.0888 0.7506
10.750 1.2728 0.03731 0.03070 -0.0927 0.0781 0.7538
11.250 1.2909 0.04022 0.03355 -0.0902 0.0551 0.7599
11.500 1.2987 0.04180 0.03509 -0.0890 0.0419 0.7634
11.750 1.3086 0.04325 0.03651 -0.0879 0.0341 0.7673
12.000 1.3167 0.04487 0.03810 -0.0868 0.0253 0.7708
12.250 1.3263 0.04639 0.03961 -0.0858 0.0188 0.7744
12.500 1.3361 0.04791 0.04114 -0.0849 0.0142 0.7783
12.750 1.3457 0.04948 0.04272 -0.0840 0.0106 0.7822
13.000 1.3573 0.05088 0.04416 -0.0834 0.0089 0.7859
13.250 1.3686 0.05231 0.04564 -0.0827 0.0074 0.7897
13.500 1.3784 0.05392 0.04729 -0.0820 0.0059 0.7941
13.750 1.3890 0.05547 0.04889 -0.0813 0.0046 0.7988
14.000 1.3996 0.05703 0.05049 -0.0807 0.0036 0.8033
14.250 1.4099 0.05864 0.05218 -0.0802 0.0030 0.8084
14.500 1.4194 0.06036 0.05396 -0.0796 0.0023 0.8137
14.750 1.4277 0.06218 0.05583 -0.0790 0.0014 0.8185
15.000 1.4369 0.06395 0.05768 -0.0784 0.0012 0.8243
15.250 1.4450 0.06589 0.05970 -0.0779 0.0009 0.8303
15.500 1.4535 0.06778 0.06167 -0.0774 0.0008 0.8368
15.750 1.4612 0.06979 0.06377 -0.0770 0.0007 0.8447
16.000 1.4689 0.07181 0.06589 -0.0766 0.0006 0.8539
16.250 1.4765 0.07382 0.06802 -0.0761 0.0006 0.8655
16.500 1.4823 0.07600 0.07033 -0.0757 0.0005 0.8832
16.750 1.4856 0.07797 0.07252 -0.0747 0.0005 1.0000
17.000 1.4916 0.08031 0.07494 -0.0745 0.0004 1.0000
17.250 1.4968 0.08279 0.07750 -0.0743 0.0004 1.0000
17.500 1.5015 0.08534 0.08013 -0.0742 0.0004 1.0000
17.750 1.5040 0.08823 0.08312 -0.0741 0.0003 1.0000
18.000 1.5063 0.09114 0.08613 -0.0741 0.0003 1.0000
18.250 1.5064 0.09440 0.08949 -0.0741 0.0003 1.0000
18.500 1.5073 0.09760 0.09280 -0.0743 0.0003 1.0000
18.750 1.5087 0.10075 0.09604 -0.0746 0.0003 1.0000
19.000 1.5046 0.10475 0.10017 -0.0750 0.0003 1.0000
19.250 1.5042 0.10825 0.10377 -0.0756 0.0003 1.0000
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