NREL's S835 Airfoil (s835-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S835 Airfoil (s835-nr) Reynolds number: 100,000 Max Cl/Cd: 34.84 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s835-nr-100000.txt Download as CSV file: xf-s835-nr-100000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S835 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4639 0.10993 0.10313 -0.0206 1.0000 0.3006
-8.750 -0.4883 0.10511 0.09829 -0.0202 1.0000 0.3012
-8.500 -1.0629 0.04507 0.03765 -0.0183 1.0000 0.3228
-8.250 -1.0267 0.04694 0.03973 -0.0169 1.0000 0.3253
-8.000 -0.9949 0.04863 0.04154 -0.0153 1.0000 0.3281
-7.750 -0.9775 0.04892 0.04186 -0.0136 1.0000 0.3317
-7.500 -1.0232 0.04094 0.03323 -0.0140 1.0000 0.3414
-7.250 -1.0007 0.04162 0.03408 -0.0123 1.0000 0.3441
-7.000 -0.9809 0.04209 0.03463 -0.0107 1.0000 0.3475
-6.750 -0.9671 0.04152 0.03402 -0.0098 1.0000 0.3523
-6.500 -0.9634 0.03818 0.03025 -0.0112 1.0000 0.3604
-6.250 -0.9439 0.03858 0.03080 -0.0095 1.0000 0.3634
-6.000 -0.9256 0.03880 0.03108 -0.0082 1.0000 0.3672
-5.750 -0.9094 0.03817 0.03038 -0.0079 1.0000 0.3726
-5.500 -0.8497 0.03799 0.02996 -0.0162 0.9841 0.3814
-5.250 -0.8050 0.03913 0.03121 -0.0190 0.9731 0.3861
-5.000 -0.7654 0.03922 0.03120 -0.0225 0.9657 0.3933
-4.750 -0.7381 0.03804 0.02983 -0.0247 0.9564 0.4003
-4.500 -0.6959 0.03913 0.03104 -0.0270 0.9505 0.4048
-4.250 -0.6774 0.03873 0.03063 -0.0262 0.9429 0.4101
-4.000 -0.6417 0.03785 0.02951 -0.0301 0.9373 0.4191
-3.750 -0.6175 0.03816 0.02994 -0.0295 0.9295 0.4229
-3.500 -0.5855 0.03847 0.03029 -0.0306 0.9234 0.4286
-3.250 -0.5526 0.03766 0.02921 -0.0339 0.9178 0.4383
-3.000 -0.5312 0.03792 0.02963 -0.0327 0.9106 0.4421
-2.750 -0.4927 0.03846 0.03023 -0.0346 0.9054 0.4479
-2.500 -0.4721 0.03781 0.02942 -0.0352 0.8981 0.4564
-2.250 -0.4426 0.03796 0.02965 -0.0359 0.8920 0.4619
-2.000 -0.4001 0.03865 0.03043 -0.0382 0.8877 0.4682
-1.750 -0.3880 0.03807 0.02973 -0.0373 0.8789 0.4761
-1.500 -0.3539 0.03822 0.02994 -0.0387 0.8735 0.4824
-1.250 -0.3268 0.03868 0.03048 -0.0386 0.8671 0.4881
-1.000 -0.3024 0.03841 0.03011 -0.0395 0.8596 0.4976
-0.750 -0.2664 0.03871 0.03050 -0.0409 0.8548 0.5035
-0.500 -0.2465 0.03906 0.03093 -0.0398 0.8472 0.5091
-0.250 -0.2162 0.03882 0.03057 -0.0418 0.8402 0.5197
0.000 -0.1794 0.03925 0.03114 -0.0427 0.8356 0.5251
0.250 -0.1662 0.03965 0.03162 -0.0408 0.8267 0.5310
0.500 -0.1313 0.03944 0.03131 -0.0433 0.8202 0.5419
0.750 -0.0928 0.03983 0.03186 -0.0442 0.8160 0.5472
1.000 -0.0853 0.04027 0.03236 -0.0416 0.8055 0.5533
1.250 -0.0465 0.04013 0.03217 -0.0442 0.7996 0.5641
1.500 -0.0054 0.04039 0.03258 -0.0453 0.7959 0.5700
1.750 -0.0025 0.04089 0.03313 -0.0424 0.7835 0.5765
2.000 0.0407 0.04068 0.03292 -0.0451 0.7786 0.5867
2.250 0.0548 0.04123 0.03358 -0.0430 0.7690 0.5919
2.500 0.0853 0.04131 0.03371 -0.0435 0.7613 0.6007
2.750 0.1315 0.04097 0.03342 -0.0459 0.7572 0.6099
3.000 0.1353 0.04171 0.03426 -0.0427 0.7444 0.6153
3.250 0.1803 0.04131 0.03387 -0.0454 0.7391 0.6265
3.500 0.2261 0.04082 0.03351 -0.0466 0.7359 0.6337
3.750 0.2254 0.04167 0.03445 -0.0431 0.7209 0.6398
4.000 0.2787 0.04080 0.03360 -0.0465 0.7172 0.6514
4.250 0.2812 0.04160 0.03451 -0.0430 0.7031 0.6563
4.500 0.3253 0.04082 0.03383 -0.0440 0.6984 0.6654
4.750 0.3812 0.03944 0.03253 -0.0467 0.6959 0.6756
5.500 0.4864 0.03702 0.03041 -0.0463 0.6741 0.7006
6.250 0.5658 0.03528 0.02897 -0.0429 0.6421 0.7258
6.500 0.6378 0.03249 0.02626 -0.0470 0.6388 0.7378
6.750 0.7126 0.02952 0.02341 -0.0505 0.6350 0.7461
7.000 0.7319 0.02926 0.02322 -0.0489 0.6185 0.7562
7.250 0.7593 0.02844 0.02248 -0.0474 0.6036 0.7638
7.500 0.8022 0.02722 0.02130 -0.0482 0.5873 0.7737
7.750 0.8318 0.02648 0.02057 -0.0473 0.5679 0.7826
8.000 0.8512 0.02611 0.02021 -0.0451 0.5463 0.7918
8.250 0.8689 0.02589 0.01998 -0.0429 0.5219 0.8011
8.500 0.8837 0.02572 0.01975 -0.0400 0.4967 0.8104
8.750 0.8978 0.02577 0.01970 -0.0375 0.4688 0.8202
9.000 0.9026 0.02606 0.01993 -0.0337 0.4407 0.8299
9.250 0.9127 0.02637 0.02005 -0.0307 0.4115 0.8398
9.500 0.9148 0.02699 0.02060 -0.0271 0.3825 0.8507
9.750 0.9178 0.02755 0.02101 -0.0234 0.3556 0.8610
10.000 0.9222 0.02836 0.02167 -0.0204 0.3285 0.8725
10.250 0.9235 0.02916 0.02237 -0.0169 0.3039 0.8847
10.500 0.9248 0.02996 0.02306 -0.0135 0.2813 0.8977
10.750 0.9265 0.03082 0.02379 -0.0104 0.2603 0.9123
11.000 0.9287 0.03168 0.02455 -0.0074 0.2408 0.9292
11.250 0.9341 0.03261 0.02538 -0.0053 0.2217 0.9511
11.500 0.9447 0.03377 0.02652 -0.0050 0.2013 1.0000
11.750 0.9593 0.03551 0.02817 -0.0056 0.1821 1.0000
12.000 0.9742 0.03729 0.02983 -0.0062 0.1651 1.0000
12.250 0.9897 0.03909 0.03152 -0.0068 0.1500 1.0000
12.500 1.0059 0.04091 0.03323 -0.0074 0.1369 1.0000
12.750 1.0223 0.04274 0.03499 -0.0079 0.1254 1.0000
13.000 1.0393 0.04458 0.03676 -0.0084 0.1154 1.0000
13.250 1.0580 0.04637 0.03846 -0.0089 0.1068 1.0000
13.500 1.0793 0.04803 0.03995 -0.0095 0.0992 1.0000
13.750 1.0926 0.05000 0.04202 -0.0096 0.0930 1.0000
14.000 1.1093 0.05199 0.04403 -0.0098 0.0873 1.0000
14.250 1.1356 0.05354 0.04539 -0.0105 0.0821 1.0000
14.500 1.1412 0.05601 0.04810 -0.0100 0.0783 1.0000
14.750 1.1645 0.05771 0.04966 -0.0105 0.0743 1.0000
15.000 1.1664 0.06048 0.05271 -0.0099 0.0716 1.0000
15.250 1.1878 0.06228 0.05441 -0.0102 0.0686 1.0000
15.500 1.1907 0.06538 0.05775 -0.0099 0.0667 1.0000
15.750 1.1860 0.06879 0.06143 -0.0094 0.0650 1.0000
16.000 1.1945 0.07128 0.06398 -0.0094 0.0630 1.0000
16.250 1.2090 0.07371 0.06637 -0.0097 0.0611 1.0000
16.500 1.1886 0.07837 0.07141 -0.0096 0.0605 1.0000
16.750 1.1683 0.08343 0.07681 -0.0101 0.0598 1.0000
17.000 1.1467 0.08894 0.08263 -0.0113 0.0593 1.0000
17.250 1.1224 0.09515 0.08914 -0.0132 0.0591 1.0000
17.500 1.0916 0.10258 0.09689 -0.0163 0.0591 1.0000
17.750 1.0537 0.11167 0.10632 -0.0209 0.0595 1.0000
18.000 1.0099 0.12267 0.11761 -0.0275 0.0602 1.0000
18.250 0.9671 0.13488 0.13006 -0.0353 0.0611 1.0000
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