NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S830 Airfoil (s830-nr) Reynolds number: 1,000,000 Max Cl/Cd: 115.28 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s830-nr-1000000-n5.txt Download as CSV file: xf-s830-nr-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S830 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.3612 0.05144 0.04878 -0.1589 0.9697 0.0035
-13.750 -0.3786 0.04679 0.04390 -0.1591 0.9667 0.0035
-13.500 -0.3853 0.04259 0.03945 -0.1605 0.9648 0.0035
-13.250 -0.3804 0.03936 0.03599 -0.1624 0.9633 0.0035
-13.000 -0.3734 0.03626 0.03262 -0.1640 0.9619 0.0035
-12.750 -0.3587 0.03411 0.03027 -0.1656 0.9606 0.0035
-12.500 -0.3535 0.03269 0.02871 -0.1640 0.9565 0.0035
-12.250 -0.3415 0.03183 0.02781 -0.1633 0.9515 0.0036
-12.000 -0.3230 0.03049 0.02632 -0.1640 0.9483 0.0036
-11.750 -0.3056 0.02953 0.02526 -0.1640 0.9440 0.0036
-11.500 -0.2939 0.02881 0.02448 -0.1626 0.9363 0.0036
-11.250 -0.2733 0.02795 0.02351 -0.1629 0.9288 0.0037
-11.000 -0.2480 0.02715 0.02258 -0.1639 0.9180 0.0037
-10.750 -0.2178 0.02642 0.02175 -0.1662 0.9042 0.0037
-10.500 -0.1887 0.02580 0.02093 -0.1678 0.8808 0.0038
-10.250 -0.1703 0.02536 0.02033 -0.1672 0.8615 0.0038
-10.000 -0.1548 0.02500 0.01984 -0.1662 0.8423 0.0039
-9.750 -0.1418 0.02464 0.01936 -0.1646 0.8260 0.0039
-9.500 -0.1321 0.02422 0.01883 -0.1624 0.8116 0.0040
-9.250 -0.1204 0.02381 0.01833 -0.1608 0.7997 0.0040
-9.000 -0.1102 0.02335 0.01779 -0.1589 0.7878 0.0041
-8.750 -0.0986 0.02292 0.01730 -0.1573 0.7762 0.0041
-8.500 -0.0890 0.02243 0.01675 -0.1555 0.7664 0.0042
-8.250 -0.0800 0.02192 0.01617 -0.1535 0.7562 0.0042
-8.000 -0.0708 0.02140 0.01561 -0.1517 0.7477 0.0042
-7.500 -0.0578 0.02030 0.01441 -0.1471 0.7300 0.0044
-7.250 -0.0531 0.01977 0.01382 -0.1444 0.7217 0.0044
-7.000 -0.0518 0.01914 0.01316 -0.1412 0.7134 0.0045
-6.750 -0.0615 0.01852 0.01249 -0.1360 0.7055 0.0046
-6.500 -0.0583 0.01783 0.01178 -0.1333 0.6987 0.0046
-6.000 -0.0408 0.01630 0.01016 -0.1305 0.6853 0.0049
-5.750 -0.0251 0.01551 0.00932 -0.1303 0.6788 0.0050
-5.500 -0.0051 0.01471 0.00846 -0.1310 0.6730 0.0053
-5.250 0.0196 0.01388 0.00758 -0.1326 0.6667 0.0059
-5.000 0.0461 0.01306 0.00670 -0.1346 0.6604 0.0073
-4.750 0.0779 0.01223 0.00584 -0.1376 0.6545 0.0116
-4.500 0.1079 0.01169 0.00526 -0.1396 0.6480 0.0158
-4.250 0.1364 0.01132 0.00485 -0.1409 0.6424 0.0213
-4.000 0.1663 0.01097 0.00451 -0.1423 0.6370 0.0293
-3.750 0.1953 0.01067 0.00421 -0.1436 0.6314 0.0425
-3.500 0.2250 0.01035 0.00391 -0.1449 0.6264 0.0637
-3.250 0.2866 0.00773 0.00233 -0.1568 0.6211 0.4454
-3.000 0.3142 0.00771 0.00230 -0.1571 0.6157 0.4619
-2.750 0.3411 0.00773 0.00230 -0.1573 0.6109 0.4732
-2.500 0.3687 0.00775 0.00230 -0.1575 0.6059 0.4799
-2.250 0.3950 0.00780 0.00231 -0.1575 0.6004 0.4842
-2.000 0.4210 0.00786 0.00231 -0.1574 0.5953 0.4874
-1.750 0.4482 0.00790 0.00231 -0.1576 0.5904 0.4900
-1.500 0.4747 0.00795 0.00233 -0.1577 0.5853 0.4929
-1.250 0.5006 0.00801 0.00235 -0.1576 0.5808 0.4940
-1.000 0.5281 0.00804 0.00236 -0.1578 0.5768 0.4950
-0.750 0.5550 0.00809 0.00238 -0.1580 0.5723 0.4961
-0.500 0.5811 0.00816 0.00241 -0.1579 0.5679 0.4972
-0.250 0.6074 0.00823 0.00245 -0.1580 0.5639 0.4983
0.000 0.6345 0.00828 0.00249 -0.1582 0.5601 0.4994
0.250 0.6612 0.00835 0.00253 -0.1582 0.5559 0.5005
0.500 0.6871 0.00844 0.00259 -0.1582 0.5517 0.5017
0.750 0.7134 0.00853 0.00265 -0.1582 0.5480 0.5028
1.000 0.7403 0.00860 0.00271 -0.1584 0.5441 0.5038
1.250 0.7667 0.00868 0.00279 -0.1585 0.5400 0.5050
1.500 0.7926 0.00877 0.00287 -0.1584 0.5363 0.5065
1.750 0.8185 0.00887 0.00297 -0.1584 0.5330 0.5077
2.000 0.8452 0.00894 0.00305 -0.1586 0.5300 0.5090
2.250 0.8715 0.00903 0.00315 -0.1586 0.5267 0.5103
2.500 0.8972 0.00913 0.00325 -0.1585 0.5234 0.5116
2.750 0.9223 0.00925 0.00337 -0.1584 0.5202 0.5130
3.000 0.9479 0.00936 0.00348 -0.1583 0.5173 0.5143
3.250 0.9742 0.00945 0.00359 -0.1584 0.5144 0.5156
3.500 1.0001 0.00955 0.00370 -0.1584 0.5112 0.5168
3.750 1.0254 0.00967 0.00383 -0.1583 0.5081 0.5178
4.000 1.0501 0.00980 0.00397 -0.1581 0.5052 0.5188
4.250 1.0746 0.00994 0.00412 -0.1578 0.5025 0.5201
4.500 1.1005 0.01003 0.00426 -0.1578 0.5004 0.5216
4.750 1.1260 0.01014 0.00441 -0.1578 0.4980 0.5230
5.000 1.1510 0.01026 0.00457 -0.1577 0.4954 0.5243
5.250 1.1755 0.01040 0.00475 -0.1574 0.4926 0.5257
5.500 1.1993 0.01057 0.00493 -0.1571 0.4898 0.5272
5.750 1.2228 0.01075 0.00513 -0.1566 0.4872 0.5287
6.000 1.2482 0.01087 0.00530 -0.1566 0.4851 0.5303
6.250 1.2715 0.01103 0.00550 -0.1562 0.4787 0.5316
6.500 1.2902 0.01133 0.00576 -0.1549 0.4674 0.5328
6.750 1.3078 0.01167 0.00606 -0.1534 0.4536 0.5338
7.000 1.3263 0.01201 0.00638 -0.1521 0.4413 0.5351
7.250 1.3479 0.01225 0.00665 -0.1515 0.4321 0.5365
7.500 1.3644 0.01266 0.00704 -0.1499 0.4169 0.5379
7.750 1.3807 0.01311 0.00746 -0.1483 0.4012 0.5391
8.000 1.3932 0.01373 0.00800 -0.1461 0.3789 0.5405
8.250 1.3930 0.01491 0.00897 -0.1420 0.3353 0.5416
8.500 1.3861 0.01649 0.01029 -0.1369 0.2879 0.5427
8.750 1.3851 0.01789 0.01152 -0.1330 0.2527 0.5438
9.000 1.3841 0.01935 0.01283 -0.1293 0.2206 0.5450
9.250 1.3848 0.02081 0.01417 -0.1261 0.1937 0.5460
9.500 1.3847 0.02239 0.01564 -0.1229 0.1681 0.5470
9.750 1.3824 0.02421 0.01733 -0.1196 0.1415 0.5480
10.000 1.3784 0.02624 0.01924 -0.1164 0.1150 0.5488
10.250 1.3808 0.02797 0.02091 -0.1141 0.0980 0.5498
10.500 1.3816 0.02989 0.02278 -0.1119 0.0811 0.5512
10.750 1.3833 0.03184 0.02469 -0.1099 0.0674 0.5525
11.000 1.3865 0.03374 0.02657 -0.1081 0.0566 0.5536
11.250 1.3906 0.03565 0.02847 -0.1066 0.0476 0.5548
11.500 1.3932 0.03775 0.03056 -0.1051 0.0387 0.5559
11.750 1.3951 0.03999 0.03279 -0.1036 0.0305 0.5570
12.000 1.4023 0.04181 0.03464 -0.1026 0.0272 0.5582
12.250 1.4093 0.04368 0.03655 -0.1017 0.0245 0.5594
12.500 1.4154 0.04570 0.03859 -0.1009 0.0215 0.5605
12.750 1.4201 0.04790 0.04082 -0.1000 0.0183 0.5615
13.000 1.4266 0.04995 0.04290 -0.0993 0.0159 0.5626
13.250 1.4319 0.05217 0.04515 -0.0986 0.0139 0.5637
13.500 1.4368 0.05446 0.04749 -0.0980 0.0117 0.5646
13.750 1.4433 0.05664 0.04971 -0.0975 0.0104 0.5657
14.000 1.4483 0.05902 0.05214 -0.0970 0.0089 0.5671
14.250 1.4543 0.06133 0.05451 -0.0967 0.0079 0.5684
14.500 1.4599 0.06371 0.05695 -0.0964 0.0069 0.5696
14.750 1.4647 0.06622 0.05951 -0.0961 0.0061 0.5707
15.000 1.4706 0.06861 0.06196 -0.0959 0.0054 0.5719
15.250 1.4756 0.07117 0.06458 -0.0958 0.0049 0.5731
15.500 1.4807 0.07373 0.06720 -0.0957 0.0044 0.5744
15.750 1.4859 0.07632 0.06986 -0.0957 0.0041 0.5757
16.000 1.4911 0.07890 0.07250 -0.0957 0.0036 0.5770
16.250 1.4944 0.08176 0.07542 -0.0958 0.0032 0.5782
16.500 1.4993 0.08442 0.07814 -0.0959 0.0029 0.5793
16.750 1.5034 0.08723 0.08102 -0.0961 0.0026 0.5802
17.000 1.5078 0.09001 0.08386 -0.0963 0.0022 0.5811
17.250 1.5106 0.09306 0.08698 -0.0967 0.0020 0.5824
17.500 1.5151 0.09588 0.08987 -0.0971 0.0017 0.5837
17.750 1.5180 0.09892 0.09300 -0.0975 0.0015 0.5850
18.000 1.5213 0.10191 0.09606 -0.0980 0.0013 0.5863
18.250 1.5229 0.10516 0.09939 -0.0986 0.0011 0.5878
18.500 1.5259 0.10823 0.10253 -0.0993 0.0009 0.5893
18.750 1.5282 0.11143 0.10581 -0.1000 0.0008 0.5907
19.000 1.5302 0.11463 0.10909 -0.1008 0.0007 0.5920
19.250 1.5316 0.11795 0.11248 -0.1017 0.0006 0.5933
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