NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S826 Airfoil (s826-nr) Reynolds number: 50,000 Max Cl/Cd: 34.41 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s826-nr-50000-n5.txt Download as CSV file: xf-s826-nr-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S826 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3494 0.12362 0.11659 -0.0457 1.0000 0.0501
-10.250 -0.3496 0.12003 0.11307 -0.0460 1.0000 0.0478
-9.750 -0.3668 0.11024 0.10347 -0.0499 1.0000 0.0416
-9.500 -0.3666 0.10714 0.10043 -0.0493 1.0000 0.0409
-9.250 -0.3693 0.10377 0.09714 -0.0492 1.0000 0.0403
-9.000 -0.3739 0.10027 0.09373 -0.0493 1.0000 0.0396
-8.750 -0.3811 0.09649 0.09004 -0.0496 1.0000 0.0389
-8.500 -0.3908 0.09263 0.08628 -0.0499 1.0000 0.0383
-8.250 -0.4042 0.08877 0.08252 -0.0502 1.0000 0.0376
-8.000 -0.4218 0.08517 0.07902 -0.0501 1.0000 0.0370
-7.750 -0.4447 0.08197 0.07593 -0.0494 1.0000 0.0366
-7.500 -0.4690 0.07864 0.07268 -0.0493 1.0000 0.0361
-7.250 -0.4889 0.07454 0.06858 -0.0514 1.0000 0.0356
-7.000 -0.4995 0.06937 0.06327 -0.0564 0.9984 0.0350
-6.750 -0.4792 0.06172 0.05506 -0.0679 0.9884 0.0339
-6.500 -0.4515 0.05574 0.04847 -0.0761 0.9802 0.0335
-6.250 -0.4191 0.05097 0.04314 -0.0822 0.9730 0.0336
-6.000 -0.3882 0.04760 0.03946 -0.0861 0.9656 0.0351
-5.750 -0.3516 0.04450 0.03592 -0.0904 0.9594 0.0378
-5.500 -0.3180 0.04166 0.03253 -0.0929 0.9518 0.0401
-5.250 -0.2811 0.03921 0.02955 -0.0946 0.9461 0.0419
-5.000 -0.2553 0.03743 0.02779 -0.0942 0.9379 0.0449
-4.750 -0.2224 0.03619 0.02637 -0.0945 0.9318 0.0515
-4.500 -0.2001 0.03511 0.02524 -0.0925 0.9224 0.0559
-4.250 -0.1720 0.03416 0.02416 -0.0925 0.9138 0.0654
-4.000 -0.1377 0.03288 0.02287 -0.0943 0.9067 0.0789
-3.750 -0.1014 0.03120 0.02126 -0.0981 0.8982 0.1017
-3.250 -0.0232 0.03052 0.02192 -0.1040 0.8824 0.4920
-3.000 -0.0071 0.03201 0.02332 -0.0990 0.8726 0.5261
-2.750 0.0128 0.03303 0.02420 -0.0950 0.8646 0.5541
-2.500 0.0319 0.03344 0.02446 -0.0924 0.8545 0.5709
-2.250 0.0739 0.03298 0.02361 -0.0959 0.8494 0.5794
-2.000 0.1024 0.03268 0.02308 -0.0969 0.8400 0.5812
-1.750 0.1426 0.03215 0.02227 -0.0998 0.8350 0.5830
-1.500 0.1721 0.03191 0.02182 -0.1012 0.8260 0.5854
-1.250 0.2123 0.03143 0.02111 -0.1042 0.8211 0.5885
-1.000 0.2454 0.03122 0.02070 -0.1064 0.8130 0.5922
-0.750 0.2830 0.03088 0.02018 -0.1089 0.8076 0.5951
-0.500 0.3141 0.03074 0.01993 -0.1101 0.8007 0.5977
-0.250 0.3468 0.03061 0.01969 -0.1115 0.7940 0.6010
0.000 0.3894 0.03026 0.01918 -0.1148 0.7903 0.6054
0.250 0.4157 0.03044 0.01929 -0.1157 0.7813 0.6094
0.500 0.4521 0.03025 0.01905 -0.1175 0.7769 0.6126
0.750 0.4781 0.03046 0.01921 -0.1180 0.7691 0.6164
1.000 0.5147 0.03041 0.01910 -0.1202 0.7638 0.6214
1.250 0.5552 0.03022 0.01887 -0.1228 0.7603 0.6258
1.500 0.5726 0.03078 0.01946 -0.1219 0.7512 0.6296
1.750 0.6112 0.03070 0.01936 -0.1243 0.7471 0.6347
2.000 0.6353 0.03117 0.01984 -0.1246 0.7396 0.6395
2.250 0.6648 0.03135 0.02007 -0.1253 0.7342 0.6441
2.500 0.7040 0.03128 0.02004 -0.1275 0.7308 0.6502
2.750 0.7190 0.03214 0.02096 -0.1265 0.7219 0.6550
3.000 0.7529 0.03220 0.02109 -0.1278 0.7176 0.6603
3.250 0.7741 0.03291 0.02187 -0.1277 0.7104 0.6663
3.500 0.8014 0.03325 0.02235 -0.1280 0.7045 0.6720
3.750 0.8400 0.03316 0.02236 -0.1299 0.7010 0.6792
4.000 0.8499 0.03432 0.02364 -0.1281 0.6913 0.6851
4.250 0.8863 0.03425 0.02374 -0.1295 0.6871 0.6923
4.500 0.8983 0.03535 0.02497 -0.1280 0.6777 0.6992
4.750 0.9332 0.03531 0.02510 -0.1290 0.6728 0.7073
5.000 0.9457 0.03635 0.02629 -0.1274 0.6634 0.7150
5.250 0.9822 0.03620 0.02637 -0.1285 0.6578 0.7246
5.500 0.9930 0.03718 0.02754 -0.1265 0.6476 0.7329
5.750 1.0367 0.03657 0.02715 -0.1283 0.6419 0.7448
6.000 1.0467 0.03750 0.02831 -0.1260 0.6304 0.7554
6.250 1.0683 0.03773 0.02878 -0.1248 0.6202 0.7676
6.500 1.1140 0.03661 0.02793 -0.1262 0.6116 0.7839
6.750 1.1278 0.03702 0.02859 -0.1239 0.5987 0.7999
7.000 1.1434 0.03712 0.02900 -0.1215 0.5856 0.8196
7.250 1.1604 0.03699 0.02914 -0.1192 0.5722 0.8473
7.750 1.2006 0.03639 0.02903 -0.1155 0.5412 1.0000
8.000 1.2323 0.03581 0.02863 -0.1152 0.5224 1.0000
8.250 1.2376 0.03668 0.02965 -0.1123 0.5020 1.0000
8.500 1.2492 0.03708 0.03020 -0.1098 0.4793 1.0000
8.750 1.2494 0.03833 0.03161 -0.1066 0.4541 1.0000
9.000 1.2521 0.03949 0.03290 -0.1037 0.4244 1.0000
9.250 1.2605 0.04020 0.03363 -0.1012 0.3873 1.0000
9.500 1.2720 0.04073 0.03392 -0.0986 0.3408 1.0000
9.750 1.2747 0.04238 0.03527 -0.0960 0.2976 1.0000
10.000 1.2719 0.04485 0.03749 -0.0936 0.2626 1.0000
10.250 1.2679 0.04768 0.04014 -0.0916 0.2337 1.0000
10.500 1.2642 0.05070 0.04303 -0.0900 0.2088 1.0000
10.750 1.2610 0.05381 0.04603 -0.0887 0.1882 1.0000
11.000 1.2596 0.05690 0.04907 -0.0876 0.1693 1.0000
11.250 1.2590 0.06001 0.05215 -0.0867 0.1523 1.0000
11.500 1.2598 0.06307 0.05520 -0.0859 0.1376 1.0000
11.750 1.2613 0.06613 0.05827 -0.0852 0.1242 1.0000
12.000 1.2641 0.06913 0.06130 -0.0846 0.1125 1.0000
12.250 1.2668 0.07217 0.06434 -0.0840 0.1019 1.0000
12.500 1.2700 0.07524 0.06751 -0.0836 0.0921 1.0000
12.750 1.2746 0.07834 0.07079 -0.0832 0.0828 1.0000
13.000 1.2790 0.08146 0.07398 -0.0829 0.0750 1.0000
13.250 1.2819 0.08477 0.07740 -0.0828 0.0680 1.0000
13.500 1.2860 0.08822 0.08108 -0.0826 0.0616 1.0000
13.750 1.2874 0.09179 0.08476 -0.0829 0.0565 1.0000
14.000 1.2889 0.09567 0.08883 -0.0831 0.0520 1.0000
14.250 1.2871 0.10016 0.09364 -0.0839 0.0483 1.0000
14.500 1.2858 0.10418 0.09773 -0.0849 0.0452 1.0000
14.750 1.2828 0.10888 0.10260 -0.0860 0.0427 1.0000
15.000 1.2732 0.11504 0.10914 -0.0883 0.0412 1.0000
15.250 1.2617 0.12167 0.11609 -0.0912 0.0401 1.0000
15.500 1.2481 0.12891 0.12361 -0.0950 0.0394 1.0000
15.750 1.2323 0.13704 0.13199 -0.0997 0.0391 1.0000
16.000 1.2130 0.14658 0.14176 -0.1057 0.0394 1.0000
16.250 1.1906 0.15799 0.15336 -0.1134 0.0402 1.0000
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