NREL's S831 Airfoil (s831-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S831 Airfoil (s831-nr) Reynolds number: 500,000 Max Cl/Cd: 112.58 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s831-nr-500000-n5.txt Download as CSV file: xf-s831-nr-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.0934 0.08653 0.08275 -0.1706 0.7790 0.0113
-11.000 0.0953 0.08297 0.07919 -0.1721 0.7759 0.0113
-10.750 0.0974 0.07952 0.07575 -0.1735 0.7723 0.0113
-10.500 0.0985 0.07596 0.07219 -0.1750 0.7689 0.0113
-10.250 0.0986 0.07216 0.06839 -0.1768 0.7656 0.0113
-10.000 0.0973 0.06792 0.06414 -0.1793 0.7626 0.0113
-9.750 0.0910 0.06311 0.05934 -0.1823 0.7595 0.0113
-9.500 0.0825 0.05920 0.05539 -0.1842 0.7561 0.0113
-8.500 0.0449 0.03135 0.02749 -0.1734 0.7381 0.0080
-8.000 0.0061 0.04221 0.03793 -0.1766 0.7378 0.0079
-7.750 0.0063 0.04005 0.03562 -0.1749 0.7353 0.0076
-7.250 0.0039 0.03099 0.02599 -0.1689 0.7304 0.0057
-7.000 0.0128 0.02856 0.02333 -0.1672 0.7281 0.0056
-6.750 0.0244 0.02579 0.02028 -0.1655 0.7260 0.0055
-6.500 0.0381 0.02248 0.01662 -0.1637 0.7240 0.0053
-6.250 0.0559 0.01956 0.01328 -0.1622 0.7223 0.0051
-6.000 0.0774 0.01761 0.01100 -0.1613 0.7207 0.0051
-5.750 0.0996 0.01637 0.00956 -0.1605 0.7190 0.0051
-5.500 0.1217 0.01551 0.00857 -0.1598 0.7173 0.0051
-5.250 0.1434 0.01478 0.00773 -0.1590 0.7154 0.0051
-5.000 0.1652 0.01418 0.00704 -0.1583 0.7135 0.0052
-4.750 0.1875 0.01367 0.00646 -0.1578 0.7116 0.0053
-4.500 0.2107 0.01324 0.00596 -0.1575 0.7097 0.0054
-4.250 0.2349 0.01286 0.00550 -0.1574 0.7081 0.0056
-4.000 0.2603 0.01255 0.00511 -0.1575 0.7067 0.0058
-3.750 0.2856 0.01220 0.00472 -0.1576 0.7052 0.0066
-3.500 0.3111 0.01196 0.00445 -0.1577 0.7037 0.0075
-3.250 0.3371 0.01170 0.00418 -0.1578 0.7022 0.0113
-3.000 0.3635 0.01150 0.00401 -0.1581 0.7006 0.0189
-2.750 0.3902 0.01134 0.00390 -0.1585 0.6991 0.0307
-2.500 0.4173 0.01120 0.00380 -0.1589 0.6976 0.0459
-2.250 0.4447 0.01104 0.00365 -0.1594 0.6962 0.0622
-2.000 0.4730 0.00916 0.00316 -0.1623 0.6948 0.5295
-1.750 0.5016 0.00911 0.00325 -0.1628 0.6934 0.6047
-1.500 0.5305 0.00919 0.00330 -0.1634 0.6921 0.6273
-1.250 0.5585 0.00926 0.00335 -0.1638 0.6908 0.6390
-1.000 0.5860 0.00934 0.00339 -0.1641 0.6894 0.6496
-0.750 0.6130 0.00942 0.00348 -0.1642 0.6881 0.6584
-0.500 0.6407 0.00950 0.00351 -0.1646 0.6867 0.6648
-0.250 0.6680 0.00955 0.00356 -0.1649 0.6853 0.6679
0.000 0.6956 0.00959 0.00359 -0.1652 0.6840 0.6697
0.250 0.7234 0.00965 0.00362 -0.1657 0.6828 0.6718
0.500 0.7513 0.00970 0.00365 -0.1661 0.6815 0.6740
0.750 0.7795 0.00976 0.00368 -0.1666 0.6803 0.6761
1.000 0.8082 0.00983 0.00372 -0.1673 0.6791 0.6781
1.250 0.8373 0.00990 0.00376 -0.1680 0.6779 0.6800
1.500 0.8653 0.00997 0.00384 -0.1685 0.6767 0.6817
1.750 0.8911 0.01004 0.00395 -0.1686 0.6755 0.6835
2.000 0.9172 0.01012 0.00406 -0.1687 0.6742 0.6855
2.250 0.9435 0.01020 0.00417 -0.1688 0.6729 0.6877
2.500 0.9699 0.01028 0.00429 -0.1690 0.6716 0.6902
2.750 0.9965 0.01037 0.00440 -0.1693 0.6703 0.6927
3.250 1.0495 0.01054 0.00462 -0.1697 0.6676 0.6969
3.500 1.0763 0.01062 0.00476 -0.1700 0.6663 0.6989
3.750 1.1038 0.01072 0.00489 -0.1704 0.6653 0.7011
4.000 1.1322 0.01082 0.00502 -0.1711 0.6642 0.7034
4.250 1.1615 0.01094 0.00517 -0.1719 0.6632 0.7059
4.500 1.1868 0.01106 0.00535 -0.1719 0.6620 0.7085
4.750 1.2089 0.01119 0.00556 -0.1713 0.6604 0.7111
5.000 1.2318 0.01131 0.00578 -0.1708 0.6589 0.7134
5.250 1.2552 0.01144 0.00600 -0.1704 0.6574 0.7159
5.500 1.2783 0.01157 0.00620 -0.1699 0.6558 0.7185
5.750 1.2982 0.01161 0.00629 -0.1687 0.6524 0.7213
6.000 1.3078 0.01162 0.00634 -0.1653 0.6452 0.7243
6.250 1.3138 0.01167 0.00637 -0.1611 0.6345 0.7271
6.500 1.3139 0.01192 0.00671 -0.1559 0.6229 0.7300
6.750 1.3233 0.01219 0.00704 -0.1528 0.6133 0.7333
7.000 1.3381 0.01244 0.00731 -0.1508 0.6060 0.7366
7.250 1.3505 0.01279 0.00775 -0.1484 0.5978 0.7400
7.500 1.3623 0.01316 0.00818 -0.1460 0.5883 0.7429
7.750 1.3709 0.01365 0.00871 -0.1430 0.5749 0.7458
8.000 1.3746 0.01434 0.00940 -0.1393 0.5545 0.7492
8.250 1.3625 0.01569 0.01060 -0.1330 0.5173 0.7531
8.500 1.3471 0.01747 0.01222 -0.1267 0.4812 0.7569
8.750 1.3194 0.02012 0.01465 -0.1190 0.4367 0.7605
9.000 1.3006 0.02267 0.01704 -0.1132 0.3992 0.7642
9.250 1.2822 0.02544 0.01962 -0.1078 0.3598 0.7680
9.500 1.2696 0.02805 0.02207 -0.1035 0.3227 0.7715
9.750 1.2592 0.03062 0.02449 -0.0997 0.2862 0.7747
10.000 1.2509 0.03317 0.02686 -0.0964 0.2475 0.7781
10.250 1.2491 0.03532 0.02888 -0.0938 0.2169 0.7819
10.500 1.2486 0.03746 0.03088 -0.0916 0.1871 0.7858
11.000 1.2530 0.04143 0.03463 -0.0878 0.1334 0.7935
11.250 1.2583 0.04323 0.03635 -0.0864 0.1122 0.7977
11.750 1.2726 0.04663 0.03967 -0.0839 0.0808 0.8058
12.000 1.2815 0.04822 0.04126 -0.0830 0.0700 0.8103
12.250 1.2905 0.04983 0.04286 -0.0820 0.0598 0.8152
12.500 1.2998 0.05141 0.04445 -0.0811 0.0506 0.8202
12.750 1.3082 0.05310 0.04615 -0.0802 0.0421 0.8258
13.250 1.3235 0.05669 0.04973 -0.0784 0.0255 0.8376
13.500 1.3311 0.05854 0.05160 -0.0776 0.0198 0.8442
13.750 1.3381 0.06045 0.05353 -0.0768 0.0145 0.8513
14.000 1.3462 0.06226 0.05539 -0.0761 0.0113 0.8598
14.250 1.3549 0.06399 0.05722 -0.0754 0.0096 0.8713
14.500 1.3624 0.06586 0.05918 -0.0746 0.0078 0.8879
14.750 1.3678 0.06755 0.06101 -0.0736 0.0061 0.9819
15.000 1.3761 0.06949 0.06301 -0.0731 0.0053 1.0000
15.250 1.3832 0.07165 0.06523 -0.0727 0.0043 1.0000
15.500 1.3912 0.07371 0.06739 -0.0724 0.0036 1.0000
15.750 1.3974 0.07600 0.06975 -0.0721 0.0029 1.0000
16.000 1.4032 0.07837 0.07219 -0.0718 0.0025 1.0000
16.250 1.4091 0.08076 0.07467 -0.0716 0.0021 1.0000
16.500 1.4138 0.08331 0.07731 -0.0714 0.0018 1.0000
16.750 1.4166 0.08613 0.08022 -0.0711 0.0015 1.0000
17.000 1.4207 0.08884 0.08304 -0.0711 0.0014 1.0000
17.250 1.4244 0.09159 0.08591 -0.0711 0.0013 1.0000
17.500 1.4269 0.09458 0.08900 -0.0712 0.0012 1.0000
17.750 1.4291 0.09763 0.09217 -0.0714 0.0011 1.0000
18.000 1.4303 0.10085 0.09553 -0.0717 0.0010 1.0000
18.250 1.4309 0.10421 0.09901 -0.0721 0.0010 1.0000
18.500 1.4307 0.10770 0.10262 -0.0726 0.0009 1.0000
18.750 1.4302 0.11125 0.10629 -0.0733 0.0009 1.0000
19.000 1.4274 0.11521 0.11037 -0.0741 0.0009 1.0000
19.250 1.4253 0.11911 0.11440 -0.0751 0.0009 1.0000
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