NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S830 Airfoil (s830-nr) Reynolds number: 200,000 Max Cl/Cd: 66.33 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s830-nr-200000-n5.txt Download as CSV file: xf-s830-nr-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1965 0.09116 0.08738 -0.1206 0.9540 0.0134
-11.750 -0.2062 0.08458 0.08074 -0.1250 0.9500 0.0131
-11.500 -0.2167 0.07807 0.07413 -0.1300 0.9473 0.0128
-11.250 -0.2373 0.07315 0.06913 -0.1309 0.9385 0.0127
-10.750 -0.2669 0.06386 0.05958 -0.1341 0.9245 0.0122
-10.500 -0.2774 0.05889 0.05439 -0.1363 0.9198 0.0120
-10.000 -0.3223 0.04728 0.04196 -0.1322 0.8993 0.0107
-9.750 -0.3173 0.04440 0.03888 -0.1325 0.8936 0.0106
-9.500 -0.3153 0.04160 0.03582 -0.1314 0.8858 0.0106
-9.250 -0.3016 0.03885 0.03279 -0.1315 0.8804 0.0106
-9.000 -0.2738 0.03584 0.02940 -0.1327 0.8779 0.0106
-8.750 -0.2486 0.03396 0.02726 -0.1324 0.8725 0.0106
-8.500 -0.2101 0.03228 0.02528 -0.1328 0.8692 0.0108
-8.250 -0.1704 0.03120 0.02408 -0.1343 0.8663 0.0111
-8.000 -0.1278 0.03040 0.02315 -0.1364 0.8637 0.0115
-7.750 -0.0948 0.02986 0.02253 -0.1370 0.8581 0.0121
-7.500 -0.0620 0.02939 0.02197 -0.1376 0.8520 0.0129
-7.250 -0.0260 0.02884 0.02129 -0.1393 0.8472 0.0137
-7.000 -0.0079 0.02831 0.02073 -0.1385 0.8378 0.0144
-6.750 0.0185 0.02760 0.01997 -0.1398 0.8308 0.0167
-6.500 0.0314 0.02705 0.01938 -0.1386 0.8209 0.0186
-6.250 0.0481 0.02645 0.01872 -0.1380 0.8127 0.0219
-6.000 0.0567 0.02575 0.01800 -0.1363 0.8031 0.0241
-5.750 0.0629 0.02516 0.01735 -0.1340 0.7941 0.0279
-5.500 0.0681 0.02440 0.01656 -0.1319 0.7855 0.0324
-5.250 0.0599 0.02379 0.01594 -0.1271 0.7756 0.0360
-5.000 0.0684 0.02304 0.01512 -0.1257 0.7681 0.0427
-4.750 0.0685 0.02212 0.01422 -0.1232 0.7592 0.0495
-4.500 0.0820 0.02094 0.01297 -0.1237 0.7522 0.0617
-4.250 0.0960 0.01949 0.01152 -0.1250 0.7442 0.0823
-4.000 0.1514 0.01479 0.00788 -0.1423 0.7381 0.4752
-3.750 0.1755 0.01554 0.00862 -0.1410 0.7311 0.4951
-3.500 0.2044 0.01616 0.00911 -0.1409 0.7250 0.5073
-3.250 0.2295 0.01690 0.00980 -0.1397 0.7188 0.5142
-3.000 0.2567 0.01715 0.00992 -0.1398 0.7122 0.5208
-2.750 0.2811 0.01810 0.01085 -0.1378 0.7069 0.5237
-2.500 0.3042 0.01829 0.01099 -0.1370 0.7006 0.5259
-2.250 0.3332 0.01800 0.01056 -0.1381 0.6949 0.5275
-2.000 0.3646 0.01763 0.01002 -0.1399 0.6899 0.5292
-1.750 0.3928 0.01722 0.00948 -0.1411 0.6836 0.5312
-1.500 0.4261 0.01674 0.00880 -0.1436 0.6780 0.5337
-1.250 0.4540 0.01664 0.00861 -0.1442 0.6726 0.5345
-1.000 0.4792 0.01661 0.00853 -0.1441 0.6666 0.5352
-0.750 0.5071 0.01659 0.00844 -0.1445 0.6617 0.5358
-0.500 0.5340 0.01659 0.00839 -0.1448 0.6568 0.5366
-0.250 0.5594 0.01659 0.00837 -0.1448 0.6514 0.5374
0.000 0.5869 0.01661 0.00833 -0.1451 0.6467 0.5385
0.250 0.6149 0.01663 0.00830 -0.1456 0.6423 0.5396
0.500 0.6399 0.01664 0.00831 -0.1456 0.6370 0.5410
0.750 0.6672 0.01665 0.00827 -0.1460 0.6321 0.5424
1.250 0.7227 0.01662 0.00815 -0.1472 0.6228 0.5458
1.500 0.7508 0.01659 0.00807 -0.1480 0.6182 0.5477
1.750 0.7811 0.01658 0.00797 -0.1491 0.6143 0.5496
2.000 0.8076 0.01667 0.00807 -0.1493 0.6105 0.5504
2.250 0.8311 0.01676 0.00822 -0.1489 0.6061 0.5513
2.500 0.8565 0.01687 0.00836 -0.1488 0.6021 0.5523
2.750 0.8841 0.01697 0.00846 -0.1492 0.5985 0.5534
3.000 0.9104 0.01709 0.00859 -0.1494 0.5948 0.5546
3.250 0.9331 0.01720 0.00877 -0.1489 0.5904 0.5560
3.500 0.9582 0.01731 0.00890 -0.1488 0.5865 0.5575
3.750 0.9863 0.01743 0.00902 -0.1494 0.5833 0.5594
4.000 1.0162 0.01756 0.00914 -0.1504 0.5804 0.5615
4.250 1.0391 0.01768 0.00932 -0.1500 0.5767 0.5638
4.500 1.0633 0.01782 0.00951 -0.1499 0.5731 0.5655
4.750 1.0877 0.01798 0.00975 -0.1497 0.5698 0.5666
5.000 1.1152 0.01815 0.00995 -0.1501 0.5668 0.5677
5.250 1.1409 0.01834 0.01021 -0.1501 0.5638 0.5690
5.500 1.1614 0.01855 0.01055 -0.1492 0.5604 0.5704
5.750 1.1843 0.01876 0.01086 -0.1488 0.5573 0.5719
6.000 1.2091 0.01897 0.01114 -0.1488 0.5544 0.5737
6.250 1.2370 0.01916 0.01138 -0.1493 0.5516 0.5755
6.500 1.2660 0.01936 0.01163 -0.1501 0.5489 0.5776
6.750 1.2851 0.01966 0.01204 -0.1491 0.5456 0.5797
7.000 1.3064 0.01995 0.01245 -0.1484 0.5425 0.5814
7.250 1.3285 0.02022 0.01286 -0.1478 0.5393 0.5828
7.500 1.3537 0.02044 0.01318 -0.1478 0.5361 0.5844
7.750 1.3744 0.02072 0.01357 -0.1470 0.5317 0.5860
8.000 1.3825 0.02106 0.01404 -0.1438 0.5239 0.5876
8.250 1.3929 0.02132 0.01435 -0.1410 0.5139 0.5894
8.500 1.4035 0.02158 0.01460 -0.1383 0.5025 0.5912
8.750 1.4074 0.02212 0.01527 -0.1347 0.4920 0.5929
9.000 1.4184 0.02259 0.01580 -0.1324 0.4826 0.5948
9.250 1.4294 0.02310 0.01634 -0.1302 0.4726 0.5967
9.500 1.4350 0.02380 0.01719 -0.1272 0.4618 0.5979
9.750 1.4422 0.02452 0.01801 -0.1245 0.4506 0.5994
10.000 1.4483 0.02535 0.01892 -0.1218 0.4382 0.6009
10.250 1.4525 0.02633 0.01999 -0.1190 0.4237 0.6026
10.500 1.4540 0.02754 0.02127 -0.1160 0.4045 0.6043
10.750 1.4509 0.02909 0.02280 -0.1126 0.3777 0.6060
11.000 1.4395 0.03129 0.02485 -0.1086 0.3413 0.6075
11.250 1.4205 0.03430 0.02765 -0.1043 0.3058 0.6088
11.500 1.4019 0.03766 0.03085 -0.1006 0.2732 0.6100
11.750 1.3849 0.04123 0.03429 -0.0976 0.2434 0.6112
12.250 1.3572 0.04856 0.04142 -0.0932 0.1902 0.6133
12.500 1.3464 0.05221 0.04502 -0.0916 0.1674 0.6143
12.750 1.3373 0.05587 0.04861 -0.0903 0.1460 0.6155
13.000 1.3303 0.05944 0.05215 -0.0893 0.1274 0.6167
13.250 1.3252 0.06291 0.05559 -0.0886 0.1104 0.6180
13.500 1.3214 0.06633 0.05899 -0.0880 0.0955 0.6195
13.750 1.3189 0.06968 0.06233 -0.0877 0.0826 0.6211
14.000 1.3178 0.07297 0.06561 -0.0874 0.0717 0.6227
14.250 1.3175 0.07620 0.06885 -0.0873 0.0627 0.6243
14.500 1.3173 0.07947 0.07215 -0.0873 0.0550 0.6259
14.750 1.3196 0.08249 0.07522 -0.0874 0.0484 0.6275
15.000 1.3209 0.08568 0.07846 -0.0875 0.0433 0.6289
15.250 1.3232 0.08875 0.08161 -0.0878 0.0388 0.6301
15.500 1.3247 0.09196 0.08489 -0.0880 0.0352 0.6315
15.750 1.3276 0.09502 0.08805 -0.0884 0.0318 0.6331
16.250 1.3314 0.10146 0.09468 -0.0893 0.0265 0.6367
16.500 1.3334 0.10473 0.09802 -0.0899 0.0242 0.6386
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