NREL's S831 Airfoil (s831-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S831 Airfoil (s831-nr) Reynolds number: 1,000,000 Max Cl/Cd: 152.66 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s831-nr-1000000.txt Download as CSV file: xf-s831-nr-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 0.1329 0.08030 0.07748 -0.1593 0.7761 0.0086
-11.500 0.1373 0.07720 0.07439 -0.1604 0.7735 0.0087
-11.250 0.0999 0.08227 0.07935 -0.1752 0.7871 0.0084
-11.000 0.1036 0.07971 0.07677 -0.1760 0.7834 0.0086
-10.750 0.1038 0.07621 0.07326 -0.1773 0.7796 0.0086
-10.500 0.1090 0.07399 0.07102 -0.1781 0.7763 0.0088
-10.250 0.1087 0.07039 0.06744 -0.1797 0.7731 0.0088
-10.000 0.1069 0.06661 0.06366 -0.1815 0.7696 0.0088
-9.750 0.1076 0.06365 0.06070 -0.1831 0.7662 0.0091
-9.500 0.0965 0.05867 0.05569 -0.1866 0.7626 0.0091
-9.250 0.0753 0.05377 0.05077 -0.1885 0.7591 0.0090
-9.000 0.0629 0.05100 0.04795 -0.1884 0.7555 0.0091
-8.750 0.0470 0.04844 0.04531 -0.1871 0.7519 0.0091
-8.500 0.0265 0.04618 0.04298 -0.1841 0.7484 0.0090
-8.250 0.0221 0.04409 0.04082 -0.1825 0.7458 0.0092
-8.000 0.0215 0.04197 0.03861 -0.1810 0.7432 0.0094
-7.750 0.0235 0.03972 0.03625 -0.1794 0.7406 0.0096
-7.500 0.0284 0.03745 0.03383 -0.1779 0.7381 0.0099
-7.250 0.0358 0.03500 0.03120 -0.1764 0.7355 0.0103
-7.000 0.0521 0.03236 0.02833 -0.1745 0.7336 0.0112
-6.750 0.0648 0.03013 0.02590 -0.1728 0.7316 0.0113
-6.500 0.0773 0.02790 0.02344 -0.1712 0.7295 0.0114
-5.250 0.1673 0.01509 0.00930 -0.1656 0.7197 0.0084
-5.000 0.1887 0.01325 0.00736 -0.1645 0.7183 0.0074
-4.750 0.2101 0.01219 0.00619 -0.1635 0.7167 0.0069
-4.500 0.2326 0.01151 0.00543 -0.1629 0.7150 0.0067
-4.250 0.2563 0.01099 0.00483 -0.1627 0.7134 0.0066
-4.000 0.2814 0.01058 0.00437 -0.1627 0.7118 0.0066
-3.750 0.3075 0.01024 0.00397 -0.1629 0.7102 0.0069
-3.500 0.3346 0.00998 0.00366 -0.1633 0.7086 0.0071
-3.250 0.3629 0.00979 0.00340 -0.1639 0.7068 0.0079
-3.000 0.3907 0.00951 0.00311 -0.1644 0.7053 0.0143
-2.750 0.4178 0.00931 0.00301 -0.1648 0.7040 0.0332
-2.500 0.4455 0.00920 0.00293 -0.1653 0.7026 0.0448
-2.250 0.4734 0.00906 0.00283 -0.1658 0.7012 0.0624
-2.000 0.5019 0.00719 0.00243 -0.1685 0.6998 0.5692
-1.750 0.5307 0.00718 0.00253 -0.1691 0.6985 0.6244
-1.500 0.5594 0.00725 0.00258 -0.1696 0.6971 0.6404
-1.250 0.5884 0.00733 0.00261 -0.1702 0.6959 0.6500
-1.000 0.6173 0.00740 0.00267 -0.1708 0.6945 0.6568
-0.750 0.6470 0.00751 0.00272 -0.1716 0.6931 0.6624
-0.500 0.6773 0.00762 0.00281 -0.1725 0.6915 0.6685
-0.250 0.7049 0.00766 0.00286 -0.1728 0.6906 0.6721
0.000 0.7326 0.00770 0.00290 -0.1732 0.6894 0.6757
0.250 0.7607 0.00774 0.00292 -0.1736 0.6882 0.6775
0.500 0.7889 0.00778 0.00295 -0.1742 0.6869 0.6792
0.750 0.8172 0.00780 0.00297 -0.1747 0.6856 0.6812
1.000 0.8455 0.00783 0.00301 -0.1753 0.6844 0.6831
1.250 0.8740 0.00787 0.00306 -0.1759 0.6832 0.6851
1.500 0.9025 0.00793 0.00312 -0.1764 0.6821 0.6872
1.750 0.9311 0.00799 0.00318 -0.1771 0.6810 0.6894
2.000 0.9601 0.00806 0.00325 -0.1778 0.6798 0.6916
2.250 0.9901 0.00817 0.00334 -0.1788 0.6784 0.6936
2.500 1.0202 0.00829 0.00346 -0.1798 0.6770 0.6954
2.750 1.0466 0.00831 0.00354 -0.1799 0.6761 0.6977
3.000 1.0735 0.00836 0.00363 -0.1802 0.6751 0.6999
3.250 1.1005 0.00842 0.00375 -0.1805 0.6740 0.7020
3.500 1.1277 0.00849 0.00386 -0.1809 0.6728 0.7043
3.750 1.1550 0.00857 0.00396 -0.1813 0.6716 0.7068
4.000 1.1825 0.00864 0.00407 -0.1817 0.6702 0.7092
4.250 1.2102 0.00870 0.00417 -0.1822 0.6690 0.7115
4.500 1.2382 0.00877 0.00428 -0.1828 0.6679 0.7140
4.750 1.2658 0.00883 0.00439 -0.1832 0.6663 0.7163
5.000 1.2901 0.00887 0.00444 -0.1829 0.6615 0.7187
5.250 1.3015 0.00874 0.00436 -0.1797 0.6545 0.7215
5.500 1.3181 0.00874 0.00433 -0.1776 0.6474 0.7241
5.750 1.3244 0.00873 0.00439 -0.1734 0.6415 0.7269
6.000 1.3420 0.00880 0.00450 -0.1717 0.6368 0.7298
6.250 1.3608 0.00892 0.00467 -0.1703 0.6324 0.7327
6.500 1.3785 0.00903 0.00485 -0.1687 0.6283 0.7358
6.750 1.3963 0.00917 0.00503 -0.1671 0.6234 0.7388
7.000 1.4128 0.00934 0.00524 -0.1653 0.6173 0.7415
7.250 1.4285 0.00950 0.00547 -0.1634 0.6101 0.7447
7.500 1.4423 0.00974 0.00576 -0.1611 0.6015 0.7478
7.750 1.4527 0.01008 0.00611 -0.1582 0.5894 0.7512
8.000 1.4600 0.01055 0.00658 -0.1548 0.5713 0.7548
8.250 1.4562 0.01139 0.00733 -0.1495 0.5425 0.7584
8.500 1.4349 0.01299 0.00875 -0.1413 0.4980 0.7624
8.750 1.4050 0.01532 0.01083 -0.1324 0.4497 0.7665
9.000 1.3840 0.01763 0.01295 -0.1255 0.4081 0.7704
9.250 1.3579 0.02047 0.01556 -0.1184 0.3603 0.7742
9.500 1.3413 0.02303 0.01795 -0.1130 0.3186 0.7780
9.750 1.3288 0.02551 0.02024 -0.1085 0.2793 0.7819
10.000 1.3205 0.02786 0.02242 -0.1048 0.2439 0.7859
10.250 1.3154 0.03006 0.02448 -0.1016 0.2101 0.7898
10.500 1.3143 0.03206 0.02636 -0.0990 0.1810 0.7939
10.750 1.3144 0.03407 0.02823 -0.0966 0.1534 0.7980
11.000 1.3168 0.03594 0.03000 -0.0946 0.1310 0.8020
11.250 1.3181 0.03792 0.03186 -0.0925 0.1049 0.8061
11.500 1.3221 0.03977 0.03362 -0.0908 0.0844 0.8107
11.750 1.3291 0.04141 0.03520 -0.0895 0.0704 0.8155
12.500 1.3521 0.04631 0.03999 -0.0859 0.0366 0.8314
12.750 1.3600 0.04796 0.04164 -0.0848 0.0288 0.8374
13.000 1.3701 0.04947 0.04318 -0.0840 0.0240 0.8441
13.250 1.3793 0.05104 0.04478 -0.0831 0.0191 0.8513
13.500 1.3878 0.05270 0.04646 -0.0822 0.0151 0.8601
13.750 1.3955 0.05443 0.04823 -0.0812 0.0117 0.8715
14.000 1.4044 0.05598 0.04987 -0.0803 0.0092 0.8894
14.250 1.4118 0.05742 0.05149 -0.0792 0.0076 1.0000
14.500 1.4192 0.05939 0.05349 -0.0785 0.0055 1.0000
14.750 1.4226 0.06179 0.05589 -0.0775 0.0027 1.0000
15.000 1.4303 0.06374 0.05792 -0.0769 0.0022 1.0000
15.250 1.4368 0.06588 0.06012 -0.0763 0.0018 1.0000
15.500 1.4425 0.06812 0.06244 -0.0757 0.0016 1.0000
15.750 1.4462 0.07066 0.06507 -0.0750 0.0014 1.0000
16.000 1.4530 0.07286 0.06735 -0.0746 0.0014 1.0000
16.250 1.4579 0.07530 0.06989 -0.0742 0.0013 1.0000
16.500 1.4622 0.07786 0.07253 -0.0739 0.0012 1.0000
16.750 1.4658 0.08053 0.07529 -0.0735 0.0012 1.0000
17.000 1.4684 0.08339 0.07825 -0.0733 0.0012 1.0000
17.250 1.4713 0.08623 0.08118 -0.0732 0.0011 1.0000
17.500 1.4726 0.08933 0.08439 -0.0731 0.0011 1.0000
17.750 1.4735 0.09250 0.08766 -0.0731 0.0011 1.0000
18.000 1.4739 0.09578 0.09103 -0.0732 0.0010 1.0000
18.250 1.4725 0.09938 0.09474 -0.0735 0.0010 1.0000
18.500 1.4719 0.10290 0.09837 -0.0739 0.0010 1.0000
18.750 1.4717 0.10639 0.10195 -0.0744 0.0009 1.0000
19.000 1.4675 0.11054 0.10622 -0.0751 0.0009 1.0000
19.250 1.4646 0.11451 0.11030 -0.0759 0.0009 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S831 Airfoil (s831-nr)