NREL's S825 Airfoil (s825-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S825 Airfoil (s825-nr) Reynolds number: 500,000 Max Cl/Cd: 93.96 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s825-nr-500000-n5.txt Download as CSV file: xf-s825-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S825 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6675 0.11293 0.11005 -0.0452 1.0000 0.0037
-15.750 -0.6946 0.10381 0.10076 -0.0492 1.0000 0.0037
-15.500 -0.7133 0.09699 0.09380 -0.0520 1.0000 0.0037
-15.250 -0.7234 0.09206 0.08877 -0.0538 1.0000 0.0036
-15.000 -0.7390 0.08644 0.08299 -0.0557 1.0000 0.0037
-14.750 -0.7500 0.08179 0.07821 -0.0570 1.0000 0.0036
-14.500 -0.7604 0.07743 0.07371 -0.0581 1.0000 0.0037
-14.250 -0.7664 0.07387 0.07003 -0.0588 1.0000 0.0037
-14.000 -0.7691 0.07015 0.06616 -0.0603 0.9996 0.0037
-13.750 -0.7674 0.06702 0.06293 -0.0617 0.9991 0.0037
-13.500 -0.7641 0.06397 0.05975 -0.0632 0.9983 0.0037
-13.250 -0.7588 0.06127 0.05692 -0.0645 0.9975 0.0037
-13.000 -0.7526 0.05890 0.05445 -0.0655 0.9967 0.0038
-12.750 -0.7436 0.05673 0.05218 -0.0666 0.9957 0.0038
-12.500 -0.7329 0.05471 0.05007 -0.0679 0.9948 0.0038
-12.250 -0.7220 0.05285 0.04810 -0.0688 0.9940 0.0039
-12.000 -0.7106 0.05119 0.04638 -0.0695 0.9928 0.0039
-11.750 -0.7020 0.04948 0.04460 -0.0697 0.9912 0.0040
-11.500 -0.6895 0.04795 0.04301 -0.0705 0.9894 0.0040
-11.250 -0.6769 0.04632 0.04134 -0.0715 0.9876 0.0041
-11.000 -0.6597 0.04485 0.03983 -0.0730 0.9859 0.0042
-10.750 -0.6392 0.04340 0.03834 -0.0752 0.9843 0.0045
-10.250 -0.6045 0.04065 0.03552 -0.0778 0.9780 0.0048
-10.000 -0.5846 0.03930 0.03412 -0.0796 0.9749 0.0049
-9.750 -0.5621 0.03794 0.03272 -0.0819 0.9726 0.0054
-9.500 -0.5380 0.03657 0.03130 -0.0847 0.9709 0.0056
-9.250 -0.5398 0.03536 0.03007 -0.0824 0.9638 0.0056
-9.000 -0.5249 0.03397 0.02865 -0.0835 0.9598 0.0057
-8.750 -0.5023 0.03220 0.02686 -0.0868 0.9575 0.0063
-8.500 -0.5028 0.03067 0.02531 -0.0851 0.9484 0.0067
-8.250 -0.4770 0.02894 0.02354 -0.0887 0.9454 0.0075
-8.000 -0.4656 0.02723 0.02179 -0.0895 0.9379 0.0082
-7.750 -0.4394 0.02518 0.01972 -0.0939 0.9333 0.0093
-7.500 -0.4043 0.02311 0.01760 -0.0998 0.9310 0.0112
-7.250 -0.3833 0.02100 0.01545 -0.1030 0.9219 0.0131
-7.000 -0.3423 0.01858 0.01297 -0.1104 0.9186 0.0178
-6.750 -0.3050 0.01626 0.01059 -0.1168 0.9123 0.0246
-6.500 -0.2673 0.01477 0.00908 -0.1216 0.9064 0.0352
-6.250 -0.2293 0.01368 0.00799 -0.1254 0.9016 0.0504
-6.000 -0.1938 0.01275 0.00708 -0.1285 0.8944 0.0719
-5.750 -0.1514 0.01172 0.00613 -0.1328 0.8899 0.1083
-5.500 -0.1084 0.01056 0.00505 -0.1375 0.8829 0.1628
-5.250 -0.0560 0.00903 0.00389 -0.1446 0.8774 0.3285
-5.000 -0.0101 0.00887 0.00367 -0.1483 0.8685 0.3409
-4.750 0.0445 0.00881 0.00350 -0.1538 0.8567 0.3495
-4.500 0.0914 0.00882 0.00335 -0.1578 0.8364 0.3549
-4.250 0.1287 0.00889 0.00320 -0.1597 0.8114 0.3580
-4.000 0.1592 0.00898 0.00315 -0.1602 0.7869 0.3612
-3.750 0.1873 0.00910 0.00314 -0.1602 0.7642 0.3635
-3.500 0.2144 0.00921 0.00312 -0.1601 0.7429 0.3653
-3.250 0.2411 0.00931 0.00308 -0.1598 0.7230 0.3667
-3.000 0.2678 0.00939 0.00304 -0.1596 0.7038 0.3680
-2.750 0.2944 0.00946 0.00299 -0.1594 0.6855 0.3689
-2.500 0.3211 0.00952 0.00294 -0.1592 0.6684 0.3695
-2.250 0.3481 0.00958 0.00289 -0.1591 0.6532 0.3702
-2.000 0.3752 0.00963 0.00286 -0.1590 0.6392 0.3708
-1.750 0.4024 0.00970 0.00283 -0.1589 0.6260 0.3716
-1.500 0.4296 0.00976 0.00281 -0.1588 0.6135 0.3723
-1.250 0.4569 0.00983 0.00280 -0.1588 0.6014 0.3731
-1.000 0.4844 0.00989 0.00280 -0.1588 0.5895 0.3739
-0.750 0.5117 0.00994 0.00281 -0.1587 0.5785 0.3748
-0.500 0.5389 0.01001 0.00284 -0.1587 0.5679 0.3757
-0.250 0.5666 0.01007 0.00287 -0.1587 0.5581 0.3766
0.000 0.5941 0.01014 0.00291 -0.1587 0.5494 0.3775
0.250 0.6216 0.01021 0.00296 -0.1587 0.5408 0.3785
0.500 0.6493 0.01028 0.00301 -0.1587 0.5330 0.3795
0.750 0.6767 0.01037 0.00307 -0.1586 0.5249 0.3806
1.000 0.7043 0.01045 0.00314 -0.1586 0.5174 0.3817
1.250 0.7316 0.01054 0.00321 -0.1586 0.5099 0.3828
1.500 0.7592 0.01062 0.00329 -0.1586 0.5037 0.3840
1.750 0.7868 0.01071 0.00337 -0.1586 0.4974 0.3852
2.250 0.8416 0.01090 0.00356 -0.1585 0.4861 0.3875
2.500 0.8688 0.01100 0.00366 -0.1584 0.4801 0.3886
2.750 0.8960 0.01110 0.00379 -0.1583 0.4750 0.3900
3.000 0.9236 0.01118 0.00392 -0.1584 0.4702 0.3914
3.250 0.9507 0.01129 0.00406 -0.1583 0.4649 0.3928
3.500 0.9773 0.01143 0.00421 -0.1581 0.4579 0.3943
3.750 1.0030 0.01158 0.00435 -0.1577 0.4474 0.3959
4.000 1.0291 0.01171 0.00450 -0.1574 0.4370 0.3976
4.250 1.0547 0.01188 0.00466 -0.1570 0.4289 0.3995
4.500 1.0809 0.01201 0.00482 -0.1568 0.4207 0.4013
4.750 1.1064 0.01219 0.00499 -0.1563 0.4125 0.4029
5.000 1.1322 0.01233 0.00518 -0.1560 0.4039 0.4047
5.250 1.1576 0.01249 0.00539 -0.1556 0.3956 0.4065
5.500 1.1823 0.01269 0.00561 -0.1551 0.3855 0.4083
5.750 1.2071 0.01287 0.00582 -0.1546 0.3737 0.4103
6.000 1.2309 0.01310 0.00605 -0.1538 0.3592 0.4123
6.250 1.2531 0.01339 0.00631 -0.1529 0.3405 0.4143
6.500 1.2731 0.01377 0.00661 -0.1515 0.3120 0.4162
6.750 1.2888 0.01444 0.00706 -0.1494 0.2691 0.4179
7.000 1.3026 0.01528 0.00769 -0.1472 0.2258 0.4197
7.500 1.3336 0.01677 0.00893 -0.1432 0.1658 0.4237
7.750 1.3496 0.01744 0.00953 -0.1414 0.1442 0.4259
8.000 1.3647 0.01817 0.01017 -0.1394 0.1234 0.4281
8.250 1.3795 0.01888 0.01082 -0.1373 0.1060 0.4303
8.500 1.3941 0.01959 0.01147 -0.1353 0.0916 0.4325
8.750 1.4089 0.02028 0.01216 -0.1333 0.0800 0.4348
9.000 1.4232 0.02100 0.01289 -0.1313 0.0700 0.4373
9.250 1.4375 0.02171 0.01362 -0.1294 0.0619 0.4400
9.500 1.4508 0.02249 0.01441 -0.1273 0.0544 0.4427
9.750 1.4624 0.02338 0.01530 -0.1251 0.0472 0.4453
10.000 1.4748 0.02423 0.01617 -0.1230 0.0414 0.4477
10.250 1.4852 0.02522 0.01718 -0.1208 0.0359 0.4499
10.500 1.4961 0.02620 0.01822 -0.1187 0.0315 0.4525
10.750 1.5057 0.02729 0.01937 -0.1166 0.0279 0.4552
11.000 1.5153 0.02842 0.02055 -0.1146 0.0246 0.4580
11.250 1.5231 0.02972 0.02189 -0.1124 0.0218 0.4607
11.500 1.5311 0.03104 0.02327 -0.1105 0.0192 0.4633
11.750 1.5371 0.03259 0.02487 -0.1086 0.0168 0.4659
12.000 1.5444 0.03410 0.02647 -0.1069 0.0149 0.4689
12.250 1.5490 0.03590 0.02834 -0.1052 0.0132 0.4721
12.500 1.5545 0.03772 0.03024 -0.1037 0.0118 0.4755
12.750 1.5588 0.03973 0.03234 -0.1024 0.0105 0.4788
13.000 1.5619 0.04197 0.03468 -0.1012 0.0094 0.4821
13.250 1.5660 0.04420 0.03702 -0.1002 0.0085 0.4860
13.500 1.5685 0.04670 0.03962 -0.0994 0.0077 0.4898
13.750 1.5696 0.04947 0.04247 -0.0987 0.0070 0.4934
14.000 1.5721 0.05219 0.04532 -0.0983 0.0065 0.4970
14.250 1.5735 0.05513 0.04837 -0.0980 0.0059 0.5010
14.500 1.5737 0.05831 0.05166 -0.0979 0.0055 0.5051
14.750 1.5728 0.06174 0.05519 -0.0980 0.0050 0.5091
15.000 1.5723 0.06522 0.05881 -0.0982 0.0047 0.5133
15.250 1.5716 0.06881 0.06253 -0.0986 0.0044 0.5182
15.500 1.5702 0.07259 0.06643 -0.0991 0.0041 0.5235
15.750 1.5680 0.07658 0.07055 -0.0998 0.0039 0.5287
16.000 1.5650 0.08079 0.07490 -0.1007 0.0036 0.5347
16.500 1.5566 0.08981 0.08417 -0.1030 0.0033 0.5468
16.750 1.5534 0.09430 0.08881 -0.1043 0.0032 0.5540
17.000 1.5495 0.09897 0.09363 -0.1058 0.0030 0.5611
17.250 1.5452 0.10379 0.09859 -0.1075 0.0029 0.5688
17.500 1.5405 0.10872 0.10367 -0.1093 0.0028 0.5771
17.750 1.5356 0.11377 0.10886 -0.1113 0.0027 0.5864
18.000 1.5303 0.11895 0.11419 -0.1135 0.0026 0.5976
18.250 1.5250 0.12421 0.11961 -0.1159 0.0026 0.6097
18.500 1.5191 0.12963 0.12518 -0.1186 0.0025 0.6233
18.750 1.5130 0.13519 0.13089 -0.1214 0.0024 0.6385
19.000 1.5061 0.14100 0.13686 -0.1246 0.0024 0.6572
19.250 1.4977 0.14718 0.14322 -0.1281 0.0022 0.6784
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