NREL's S812 Airfoil (s812-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S812 Airfoil (s812-nr) Reynolds number: 100,000 Max Cl/Cd: 25.8 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s812-nr-100000-n5.txt Download as CSV file: xf-s812-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S812 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.4959 0.12223 0.11686 -0.0633 1.0000 0.0245
-15.000 -0.5056 0.11692 0.11152 -0.0652 1.0000 0.0244
-14.750 -0.5100 0.11261 0.10722 -0.0664 1.0000 0.0241
-14.500 -0.5272 0.10701 0.10156 -0.0684 1.0000 0.0240
-14.250 -0.5422 0.10207 0.09656 -0.0698 1.0000 0.0239
-14.000 -0.5598 0.09729 0.09169 -0.0709 1.0000 0.0238
-13.750 -0.5802 0.09261 0.08691 -0.0716 1.0000 0.0237
-13.500 -0.5977 0.08850 0.08269 -0.0719 1.0000 0.0236
-13.250 -0.6162 0.08461 0.07868 -0.0718 1.0000 0.0237
-13.000 -0.6345 0.08090 0.07484 -0.0713 1.0000 0.0237
-12.750 -0.6524 0.07752 0.07132 -0.0703 1.0000 0.0238
-12.500 -0.6676 0.07446 0.06813 -0.0691 1.0000 0.0238
-12.250 -0.6882 0.07162 0.06509 -0.0672 1.0000 0.0241
-12.000 -0.7000 0.06903 0.06238 -0.0653 1.0000 0.0241
-11.750 -0.7141 0.06666 0.05987 -0.0628 1.0000 0.0242
-11.500 -0.7080 0.06291 0.05582 -0.0646 0.9892 0.0243
-11.250 -0.6937 0.05918 0.05180 -0.0665 0.9763 0.0243
-11.000 -0.6759 0.05570 0.04802 -0.0678 0.9602 0.0243
-10.750 -0.6535 0.05248 0.04446 -0.0690 0.9405 0.0245
-10.500 -0.6177 0.04914 0.04087 -0.0707 0.9207 0.0249
-10.250 -0.5735 0.04662 0.03819 -0.0736 0.9020 0.0259
-10.000 -0.5304 0.04469 0.03608 -0.0773 0.8831 0.0279
-9.750 -0.4737 0.04295 0.03400 -0.0802 0.8677 0.0299
-9.500 -0.4055 0.04228 0.03297 -0.0824 0.8534 0.0313
-9.000 -0.3097 0.04243 0.03296 -0.0843 0.8231 0.0369
-8.750 -0.2552 0.04479 0.03524 -0.0832 0.8114 0.0391
-8.500 -0.2194 0.04629 0.03672 -0.0821 0.8011 0.0425
-8.250 -0.2000 0.04605 0.03642 -0.0816 0.7924 0.0454
-8.000 -0.1860 0.04529 0.03555 -0.0811 0.7850 0.0474
-7.750 -0.1750 0.04419 0.03431 -0.0806 0.7784 0.0492
-7.500 -0.1654 0.04292 0.03290 -0.0801 0.7726 0.0514
-7.250 -0.1612 0.04129 0.03121 -0.0794 0.7667 0.0548
-7.000 -0.1534 0.03986 0.02967 -0.0790 0.7617 0.0596
-6.750 -0.1475 0.03837 0.02807 -0.0783 0.7572 0.0655
-6.500 -0.1458 0.03674 0.02641 -0.0772 0.7526 0.0730
-6.250 -0.1470 0.03495 0.02463 -0.0759 0.7486 0.0887
-6.000 -0.1625 0.03235 0.02225 -0.0736 0.7450 0.1390
-5.750 -0.1921 0.03032 0.02155 -0.0683 0.7411 0.3668
-5.500 -0.1857 0.03033 0.02167 -0.0661 0.7372 0.4517
-5.250 -0.0833 0.04053 0.03172 -0.0665 0.7341 0.5061
-5.000 -0.0413 0.04235 0.03338 -0.0666 0.7312 0.5155
-4.750 -0.0257 0.04155 0.03246 -0.0662 0.7284 0.5175
-4.500 -0.0621 0.03849 0.02942 -0.0617 0.7246 0.5253
-4.250 -0.0411 0.03810 0.02895 -0.0614 0.7217 0.5261
-4.000 -0.0196 0.03778 0.02855 -0.0611 0.7191 0.5273
-3.500 -0.0424 0.03388 0.02451 -0.0564 0.7139 0.5396
-3.250 -0.0188 0.03367 0.02420 -0.0562 0.7119 0.5405
-3.000 0.0015 0.03348 0.02400 -0.0556 0.7091 0.5415
-2.750 0.0216 0.03326 0.02374 -0.0550 0.7062 0.5429
-2.250 0.0275 0.03024 0.02054 -0.0533 0.7010 0.5549
-2.000 0.0519 0.03015 0.02041 -0.0531 0.6991 0.5559
-1.750 0.0762 0.03003 0.02023 -0.0531 0.6975 0.5572
-1.500 0.0976 0.02993 0.02011 -0.0528 0.6955 0.5587
-1.250 0.1151 0.02976 0.01996 -0.0520 0.6928 0.5610
-0.750 0.1453 0.02834 0.01841 -0.0517 0.6875 0.5704
-0.500 0.1694 0.02841 0.01849 -0.0515 0.6855 0.5717
-0.250 0.1937 0.02841 0.01849 -0.0515 0.6838 0.5733
0.000 0.2185 0.02836 0.01842 -0.0516 0.6823 0.5751
0.250 0.2422 0.02825 0.01829 -0.0518 0.6806 0.5776
0.500 0.2568 0.02804 0.01811 -0.0512 0.6773 0.5815
0.750 0.2756 0.02783 0.01788 -0.0512 0.6744 0.5854
1.000 0.2971 0.02807 0.01819 -0.0506 0.6722 0.5868
1.250 0.3200 0.02826 0.01843 -0.0502 0.6702 0.5885
1.500 0.3447 0.02836 0.01856 -0.0503 0.6683 0.5907
1.750 0.3715 0.02834 0.01856 -0.0508 0.6665 0.5932
2.000 0.3947 0.02834 0.01856 -0.0512 0.6645 0.5965
2.250 0.4066 0.02858 0.01886 -0.0503 0.6606 0.6002
2.500 0.4237 0.02898 0.01936 -0.0491 0.6573 0.6016
2.750 0.4452 0.02928 0.01974 -0.0485 0.6547 0.6033
3.000 0.4698 0.02948 0.02001 -0.0485 0.6527 0.6054
3.250 0.4980 0.02956 0.02016 -0.0492 0.6509 0.6080
3.500 0.5085 0.03015 0.02084 -0.0476 0.6466 0.6111
3.750 0.5193 0.03070 0.02142 -0.0464 0.6415 0.6148
4.000 0.5424 0.03093 0.02176 -0.0462 0.6386 0.6166
4.250 0.5700 0.03104 0.02198 -0.0465 0.6364 0.6182
4.500 0.6015 0.03103 0.02206 -0.0474 0.6346 0.6202
4.750 0.5834 0.03262 0.02379 -0.0418 0.6252 0.6224
5.000 0.6121 0.03265 0.02391 -0.0424 0.6223 0.6252
5.250 0.6479 0.03243 0.02378 -0.0442 0.6202 0.6287
5.750 0.6591 0.03391 0.02547 -0.0392 0.6069 0.6330
6.000 0.6988 0.03346 0.02517 -0.0409 0.6047 0.6351
6.500 0.7156 0.03439 0.02635 -0.0363 0.5904 0.6399
6.750 0.7551 0.03363 0.02571 -0.0378 0.5864 0.6432
7.000 0.7523 0.03459 0.02674 -0.0346 0.5757 0.6462
7.250 0.7959 0.03320 0.02556 -0.0358 0.5716 0.6482
7.500 0.7916 0.03421 0.02670 -0.0322 0.5601 0.6502
7.750 0.7862 0.03553 0.02814 -0.0290 0.5473 0.6523
8.250 0.8219 0.03530 0.02818 -0.0270 0.5264 0.6581
8.500 0.8143 0.03737 0.03035 -0.0251 0.5087 0.6609
8.750 0.8192 0.03842 0.03154 -0.0235 0.4924 0.6629
9.000 0.8283 0.03912 0.03239 -0.0222 0.4747 0.6649
9.250 0.8482 0.03890 0.03231 -0.0213 0.4559 0.6673
9.500 0.8657 0.03893 0.03240 -0.0203 0.4291 0.6701
9.750 0.9143 0.03586 0.02911 -0.0199 0.3788 0.6739
10.000 0.9294 0.03603 0.02888 -0.0184 0.3249 0.6769
10.250 0.9277 0.03776 0.03039 -0.0163 0.2828 0.6787
10.500 0.9242 0.03983 0.03225 -0.0145 0.2466 0.6805
10.750 0.9226 0.04192 0.03418 -0.0132 0.2141 0.6826
11.000 0.9229 0.04397 0.03609 -0.0121 0.1857 0.6850
11.250 0.9257 0.04594 0.03795 -0.0113 0.1609 0.6876
11.500 0.9304 0.04786 0.03978 -0.0108 0.1398 0.6905
11.750 0.9355 0.04976 0.04165 -0.0102 0.1226 0.6929
12.000 0.9408 0.05164 0.04353 -0.0096 0.1087 0.6951
12.250 0.9468 0.05353 0.04542 -0.0091 0.0972 0.6975
12.500 0.9528 0.05550 0.04738 -0.0088 0.0884 0.7000
12.750 0.9603 0.05744 0.04937 -0.0086 0.0801 0.7027
13.000 0.9682 0.05939 0.05136 -0.0085 0.0734 0.7055
13.250 0.9753 0.06142 0.05345 -0.0084 0.0676 0.7081
13.500 0.9822 0.06343 0.05554 -0.0082 0.0622 0.7107
13.750 0.9893 0.06554 0.05777 -0.0082 0.0569 0.7135
14.000 0.9949 0.06785 0.06011 -0.0082 0.0525 0.7167
14.250 1.0023 0.07012 0.06252 -0.0086 0.0477 0.7201
14.750 1.0119 0.07521 0.06783 -0.0092 0.0399 0.7259
15.000 1.0158 0.07791 0.07064 -0.0097 0.0370 0.7290
15.250 1.0185 0.08083 0.07360 -0.0102 0.0345 0.7321
15.500 1.0245 0.08351 0.07649 -0.0107 0.0319 0.7357
15.750 1.0268 0.08663 0.07975 -0.0114 0.0296 0.7389
16.000 1.0273 0.08992 0.08313 -0.0123 0.0280 0.7421
16.250 1.0297 0.09314 0.08655 -0.0130 0.0263 0.7459
16.500 1.0309 0.09667 0.09030 -0.0141 0.0246 0.7500
16.750 1.0312 0.10031 0.09412 -0.0152 0.0234 0.7539
17.000 1.0307 0.10405 0.09801 -0.0165 0.0226 0.7578
17.250 1.0299 0.10790 0.10197 -0.0180 0.0218 0.7623
17.500 1.0299 0.11170 0.10584 -0.0196 0.0212 0.7672
17.750 1.0250 0.11648 0.11093 -0.0215 0.0207 0.7710
18.000 1.0170 0.12200 0.11675 -0.0240 0.0202 0.7752
18.250 1.0073 0.12805 0.12306 -0.0271 0.0198 0.7795
18.500 0.9956 0.13468 0.12994 -0.0308 0.0196 0.7837
18.750 0.9811 0.14212 0.13764 -0.0352 0.0195 0.7875
19.000 0.9617 0.15108 0.14685 -0.0407 0.0194 0.7909
19.250 0.9359 0.16234 0.15834 -0.0479 0.0196 0.7931
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