NREL's S825 Airfoil (s825-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S825 Airfoil (s825-nr) Reynolds number: 1,000,000 Max Cl/Cd: 118.89 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s825-nr-1000000.txt Download as CSV file: xf-s825-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S825 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6397 0.09866 0.09663 -0.0481 1.0000 0.0057
-14.250 -0.6659 0.09063 0.08846 -0.0516 1.0000 0.0056
-14.000 -0.6944 0.08282 0.08049 -0.0547 1.0000 0.0055
-13.750 -0.7113 0.07737 0.07491 -0.0565 1.0000 0.0054
-13.500 -0.7348 0.07124 0.06862 -0.0584 1.0000 0.0054
-13.250 -0.7510 0.06651 0.06374 -0.0594 1.0000 0.0053
-13.000 -0.7691 0.06182 0.05887 -0.0601 1.0000 0.0052
-12.750 -0.7807 0.05820 0.05511 -0.0601 1.0000 0.0051
-12.500 -0.7911 0.05494 0.05170 -0.0597 1.0000 0.0050
-12.250 -0.7882 0.05077 0.04725 -0.0626 0.9982 0.0048
-12.000 -0.7752 0.04822 0.04455 -0.0649 0.9964 0.0048
-11.750 -0.7583 0.04608 0.04226 -0.0672 0.9947 0.0047
-11.500 -0.7384 0.04436 0.04042 -0.0693 0.9927 0.0047
-11.250 -0.7211 0.04280 0.03877 -0.0706 0.9894 0.0047
-11.000 -0.6993 0.04136 0.03726 -0.0727 0.9870 0.0047
-10.750 -0.6759 0.04001 0.03584 -0.0750 0.9852 0.0048
-10.500 -0.6504 0.03874 0.03451 -0.0779 0.9840 0.0048
-10.250 -0.6378 0.03743 0.03317 -0.0782 0.9800 0.0048
-10.000 -0.6232 0.03611 0.03181 -0.0790 0.9761 0.0048
-9.750 -0.6032 0.03469 0.03034 -0.0812 0.9735 0.0050
-9.500 -0.5797 0.03326 0.02887 -0.0843 0.9717 0.0051
-9.250 -0.5787 0.03180 0.02738 -0.0829 0.9647 0.0051
-9.000 -0.5559 0.03001 0.02555 -0.0860 0.9613 0.0051
-8.750 -0.5269 0.02801 0.02350 -0.0909 0.9594 0.0053
-8.500 -0.4933 0.02604 0.02149 -0.0966 0.9581 0.0056
-8.250 -0.4781 0.02422 0.01962 -0.0982 0.9518 0.0058
-8.000 -0.4419 0.02079 0.01612 -0.1074 0.9486 0.0068
-7.750 -0.3991 0.01848 0.01374 -0.1150 0.9473 0.0079
-7.500 -0.3478 0.01516 0.01030 -0.1261 0.9467 0.0116
-7.250 -0.3032 0.01371 0.00883 -0.1321 0.9460 0.0176
-7.000 -0.2618 0.01281 0.00791 -0.1364 0.9454 0.0245
-6.750 -0.2201 0.01197 0.00709 -0.1405 0.9448 0.0353
-6.250 -0.1607 0.01059 0.00581 -0.1432 0.9365 0.0716
-6.000 -0.1221 0.00977 0.00513 -0.1464 0.9345 0.1137
-5.750 -0.0741 0.00757 0.00355 -0.1535 0.9337 0.3129
-5.500 -0.0382 0.00736 0.00337 -0.1552 0.9317 0.3354
-5.250 -0.0190 0.00730 0.00328 -0.1533 0.9224 0.3425
-5.000 0.0136 0.00713 0.00308 -0.1542 0.9178 0.3475
-4.750 0.0412 0.00705 0.00299 -0.1540 0.9076 0.3522
-4.500 0.0813 0.00697 0.00284 -0.1564 0.9005 0.3571
-4.250 0.1320 0.00686 0.00265 -0.1612 0.8909 0.3601
-4.000 0.1816 0.00673 0.00243 -0.1657 0.8728 0.3633
-3.750 0.2176 0.00682 0.00237 -0.1674 0.8437 0.3656
-3.500 0.2457 0.00700 0.00238 -0.1673 0.8136 0.3678
-3.250 0.2717 0.00714 0.00237 -0.1669 0.7861 0.3691
-3.000 0.2975 0.00727 0.00237 -0.1664 0.7614 0.3703
-2.750 0.3229 0.00739 0.00236 -0.1659 0.7388 0.3712
-2.500 0.3491 0.00750 0.00235 -0.1655 0.7181 0.3721
-2.250 0.3753 0.00761 0.00235 -0.1652 0.6982 0.3728
-2.000 0.4015 0.00771 0.00234 -0.1649 0.6795 0.3732
-1.000 0.5096 0.00788 0.00223 -0.1644 0.6174 0.3769
-0.750 0.5370 0.00794 0.00225 -0.1644 0.6043 0.3778
-0.500 0.5645 0.00801 0.00227 -0.1643 0.5920 0.3787
-0.250 0.5919 0.00809 0.00230 -0.1643 0.5802 0.3796
0.000 0.6191 0.00818 0.00234 -0.1642 0.5684 0.3805
0.250 0.6468 0.00825 0.00238 -0.1642 0.5576 0.3815
0.500 0.6744 0.00833 0.00243 -0.1642 0.5479 0.3827
1.000 0.7297 0.00850 0.00254 -0.1641 0.5300 0.3849
1.250 0.7569 0.00860 0.00261 -0.1641 0.5217 0.3859
1.500 0.7848 0.00867 0.00266 -0.1641 0.5139 0.3868
1.750 0.8119 0.00879 0.00274 -0.1640 0.5062 0.3876
2.000 0.8398 0.00885 0.00281 -0.1640 0.4994 0.3884
2.250 0.8673 0.00892 0.00287 -0.1640 0.4929 0.3904
2.500 0.8952 0.00897 0.00295 -0.1641 0.4868 0.3920
2.750 0.9223 0.00908 0.00305 -0.1640 0.4789 0.3935
3.000 0.9495 0.00917 0.00314 -0.1639 0.4697 0.3950
3.250 0.9759 0.00931 0.00325 -0.1637 0.4604 0.3964
3.500 1.0035 0.00939 0.00335 -0.1636 0.4535 0.3979
3.750 1.0299 0.00953 0.00348 -0.1634 0.4464 0.3994
4.000 1.0573 0.00961 0.00358 -0.1633 0.4398 0.4009
4.250 1.0837 0.00974 0.00371 -0.1631 0.4330 0.4021
4.500 1.1106 0.00985 0.00383 -0.1629 0.4267 0.4034
4.750 1.1376 0.00993 0.00395 -0.1628 0.4199 0.4060
5.000 1.1639 0.01007 0.00410 -0.1626 0.4128 0.4081
5.250 1.1903 0.01019 0.00425 -0.1623 0.4044 0.4101
5.500 1.2162 0.01033 0.00441 -0.1620 0.3962 0.4121
5.750 1.2418 0.01050 0.00458 -0.1616 0.3868 0.4142
6.000 1.2674 0.01066 0.00476 -0.1612 0.3762 0.4162
6.250 1.2921 0.01087 0.00494 -0.1607 0.3624 0.4177
6.500 1.3165 0.01110 0.00515 -0.1601 0.3443 0.4206
6.750 1.3388 0.01145 0.00542 -0.1592 0.3164 0.4231
7.000 1.3544 0.01226 0.00593 -0.1571 0.2611 0.4252
7.250 1.3682 0.01315 0.00655 -0.1548 0.2120 0.4273
7.500 1.3832 0.01389 0.00711 -0.1526 0.1776 0.4294
7.750 1.3995 0.01453 0.00761 -0.1506 0.1517 0.4314
8.000 1.4161 0.01514 0.00812 -0.1487 0.1300 0.4330
8.250 1.4319 0.01577 0.00866 -0.1467 0.1101 0.4360
8.500 1.4475 0.01641 0.00923 -0.1447 0.0928 0.4387
8.750 1.4626 0.01706 0.00982 -0.1427 0.0773 0.4412
9.000 1.4769 0.01773 0.01044 -0.1405 0.0641 0.4437
9.250 1.4913 0.01839 0.01106 -0.1384 0.0544 0.4461
9.500 1.5054 0.01908 0.01171 -0.1362 0.0460 0.4481
9.750 1.5197 0.01975 0.01238 -0.1342 0.0399 0.4512
10.000 1.5343 0.02040 0.01306 -0.1322 0.0351 0.4543
10.250 1.5472 0.02116 0.01384 -0.1301 0.0306 0.4574
10.500 1.5607 0.02189 0.01460 -0.1280 0.0272 0.4604
10.750 1.5723 0.02274 0.01546 -0.1258 0.0238 0.4631
11.000 1.5844 0.02358 0.01635 -0.1237 0.0212 0.4664
11.250 1.5953 0.02453 0.01732 -0.1216 0.0186 0.4698
11.500 1.6053 0.02554 0.01839 -0.1194 0.0164 0.4731
11.750 1.6150 0.02661 0.01950 -0.1173 0.0146 0.4764
12.000 1.6223 0.02788 0.02080 -0.1150 0.0127 0.4791
12.250 1.6315 0.02908 0.02208 -0.1131 0.0114 0.4831
12.500 1.6369 0.03060 0.02366 -0.1109 0.0099 0.4868
12.750 1.6439 0.03208 0.02521 -0.1091 0.0088 0.4907
13.000 1.6480 0.03385 0.02703 -0.1072 0.0076 0.4941
13.250 1.6516 0.03577 0.02905 -0.1055 0.0066 0.4984
13.500 1.6554 0.03777 0.03113 -0.1040 0.0058 0.5029
13.750 1.6541 0.04038 0.03381 -0.1024 0.0049 0.5071
14.000 1.6582 0.04258 0.03611 -0.1014 0.0045 0.5120
14.250 1.6603 0.04510 0.03873 -0.1005 0.0041 0.5177
14.500 1.6599 0.04801 0.04174 -0.0997 0.0037 0.5233
14.750 1.6544 0.05169 0.04554 -0.0991 0.0033 0.5286
15.000 1.6561 0.05461 0.04859 -0.0989 0.0032 0.5358
15.250 1.6559 0.05785 0.05195 -0.0987 0.0030 0.5429
15.500 1.6550 0.06132 0.05553 -0.0988 0.0029 0.5511
15.750 1.6532 0.06501 0.05935 -0.0991 0.0027 0.5595
16.000 1.6502 0.06893 0.06339 -0.0996 0.0026 0.5690
16.250 1.6464 0.07313 0.06772 -0.1003 0.0025 0.5794
16.500 1.6412 0.07764 0.07236 -0.1012 0.0024 0.5906
16.750 1.6325 0.08280 0.07767 -0.1024 0.0023 0.6023
17.000 1.6168 0.08924 0.08429 -0.1042 0.0022 0.6127
17.250 1.6084 0.09469 0.08989 -0.1059 0.0021 0.6280
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