NREL's S825 Airfoil (s825-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S825 Airfoil (s825-nr) Reynolds number: 100,000 Max Cl/Cd: 50.33 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s825-nr-100000.txt Download as CSV file: xf-s825-nr-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4150 0.09128 0.08685 -0.0544 1.0000 0.0677
-10.750 -0.4714 0.08061 0.07613 -0.0595 1.0000 0.0656
-10.500 -0.5140 0.07387 0.06929 -0.0620 1.0000 0.0649
-10.250 -0.5362 0.06896 0.06427 -0.0623 1.0000 0.0607
-10.000 -0.5539 0.06453 0.05981 -0.0620 1.0000 0.0594
-9.750 -0.5793 0.06052 0.05574 -0.0614 1.0000 0.0585
-9.500 -0.6062 0.05735 0.05253 -0.0600 1.0000 0.0579
-9.250 -0.7063 0.06529 0.05996 -0.0639 1.0000 0.0607
-9.000 -0.7096 0.06099 0.05555 -0.0637 1.0000 0.0578
-8.750 -0.7190 0.05612 0.04984 -0.0662 1.0000 0.0504
-8.500 -0.7110 0.05179 0.04543 -0.0655 1.0000 0.0491
-8.250 -0.7010 0.04827 0.04169 -0.0652 1.0000 0.0480
-8.000 -0.6880 0.04509 0.03826 -0.0648 1.0000 0.0472
-7.750 -0.6729 0.04241 0.03533 -0.0638 1.0000 0.0470
-7.500 -0.6570 0.04021 0.03293 -0.0623 1.0000 0.0474
-7.250 -0.6403 0.03858 0.03108 -0.0610 1.0000 0.0492
-7.000 -0.6256 0.03702 0.02940 -0.0587 1.0000 0.0520
-6.750 -0.6146 0.03603 0.02858 -0.0552 1.0000 0.0550
-6.500 -0.6031 0.03544 0.02802 -0.0515 1.0000 0.0577
-6.250 -0.5887 0.03486 0.02734 -0.0491 1.0000 0.0624
-6.000 -0.5885 0.03574 0.02857 -0.0408 1.0000 0.0674
-5.750 -0.5808 0.03673 0.02965 -0.0349 1.0000 0.0745
-5.500 -0.5584 0.03873 0.03184 -0.0305 0.9959 0.0896
-5.250 -0.4560 0.03238 0.02697 -0.0616 0.9903 0.3647
-5.000 -0.4418 0.04742 0.04223 -0.0377 0.9736 0.4070
-4.750 -0.3883 0.06646 0.06133 -0.0042 0.9709 0.5400
-4.500 -0.3134 0.06520 0.05974 -0.0047 0.9709 0.5630
-4.250 -0.2922 0.06451 0.05891 -0.0067 0.9587 0.5729
-4.000 -0.2503 0.06334 0.05756 -0.0096 0.9501 0.5814
-3.750 -0.2282 0.06235 0.05646 -0.0116 0.9387 0.5880
-3.500 -0.1790 0.06076 0.05469 -0.0159 0.9325 0.5927
-3.250 -0.1699 0.06043 0.05429 -0.0172 0.9184 0.6015
-3.000 -0.1338 0.05861 0.05238 -0.0189 0.9090 0.6034
-2.750 -0.0876 0.05694 0.05057 -0.0234 0.9038 0.6057
-2.500 -0.0781 0.05697 0.05054 -0.0252 0.8893 0.6158
-2.250 -0.0517 0.05519 0.04870 -0.0256 0.8779 0.6166
-2.000 -0.0196 0.05354 0.04699 -0.0272 0.8687 0.6177
-1.750 0.0219 0.05183 0.04519 -0.0305 0.8624 0.6195
-1.500 0.0503 0.05058 0.04390 -0.0315 0.8520 0.6226
-1.250 0.0837 0.04945 0.04269 -0.0357 0.8456 0.6317
-1.000 0.1100 0.04794 0.04116 -0.0355 0.8346 0.6335
-0.750 0.1597 0.04602 0.03918 -0.0400 0.8312 0.6360
-0.500 0.1768 0.04565 0.03878 -0.0409 0.8186 0.6465
-0.250 0.2328 0.04345 0.03652 -0.0462 0.8158 0.6481
0.000 0.2638 0.04221 0.03527 -0.0471 0.8048 0.6513
0.250 0.3231 0.04103 0.03402 -0.0554 0.8001 0.6619
0.500 0.3547 0.03967 0.03265 -0.0561 0.7883 0.6644
0.750 0.3947 0.03858 0.03153 -0.0590 0.7784 0.6694
1.000 0.4410 0.03754 0.03044 -0.0640 0.7699 0.6788
1.250 0.4667 0.03679 0.02969 -0.0639 0.7575 0.6840
1.500 0.4881 0.03631 0.02920 -0.0639 0.7458 0.6945
1.750 0.5204 0.03587 0.02872 -0.0658 0.7362 0.7074
2.000 0.5474 0.03495 0.02781 -0.0656 0.7258 0.7123
2.250 0.5609 0.03466 0.02756 -0.0635 0.7155 0.7255
2.500 0.5974 0.03399 0.02684 -0.0655 0.7078 0.7396
2.750 0.7741 0.02943 0.02161 -0.1247 0.6927 0.5391
3.000 0.8012 0.02928 0.02152 -0.1261 0.6826 0.5390
3.250 0.8405 0.02893 0.02115 -0.1297 0.6748 0.5391
3.500 0.8714 0.02878 0.02104 -0.1316 0.6658 0.5391
3.750 0.9079 0.02862 0.02088 -0.1346 0.6584 0.5396
4.000 0.9382 0.02858 0.02092 -0.1362 0.6501 0.5405
4.250 0.9668 0.02865 0.02106 -0.1368 0.6429 0.5418
4.500 0.9931 0.02876 0.02128 -0.1371 0.6346 0.5433
4.750 1.0212 0.02891 0.02152 -0.1376 0.6268 0.5455
5.000 1.0510 0.02898 0.02167 -0.1385 0.6182 0.5484
5.250 1.0795 0.02913 0.02190 -0.1394 0.6090 0.5514
5.500 1.1239 0.02884 0.02152 -0.1431 0.5997 0.5550
5.750 1.1423 0.02905 0.02194 -0.1417 0.5887 0.5568
6.000 1.1674 0.02914 0.02215 -0.1412 0.5785 0.5592
6.250 1.2024 0.02895 0.02195 -0.1424 0.5684 0.5624
6.500 1.2260 0.02905 0.02221 -0.1420 0.5564 0.5657
6.750 1.2542 0.02909 0.02231 -0.1425 0.5440 0.5698
7.000 1.2781 0.02905 0.02241 -0.1415 0.5319 0.5732
7.250 1.3040 0.02894 0.02239 -0.1408 0.5192 0.5774
7.500 1.3309 0.02879 0.02231 -0.1406 0.5050 0.5825
7.750 1.3546 0.02864 0.02224 -0.1397 0.4894 0.5869
8.000 1.3728 0.02852 0.02227 -0.1377 0.4730 0.5907
8.250 1.3897 0.02841 0.02230 -0.1356 0.4550 0.5950
8.500 1.4071 0.02828 0.02224 -0.1336 0.4348 0.6000
8.750 1.4184 0.02818 0.02224 -0.1304 0.4132 0.6039
9.000 1.4226 0.02829 0.02253 -0.1262 0.3878 0.6082
9.250 1.4224 0.02857 0.02285 -0.1213 0.3573 0.6130
9.500 1.4170 0.02921 0.02346 -0.1160 0.3186 0.6172
9.750 1.4076 0.03051 0.02450 -0.1105 0.2753 0.6208
10.000 1.3964 0.03250 0.02617 -0.1055 0.2390 0.6248
10.250 1.3872 0.03486 0.02827 -0.1015 0.2094 0.6293
10.500 1.3801 0.03727 0.03054 -0.0979 0.1854 0.6331
10.750 1.3745 0.03975 0.03290 -0.0949 0.1664 0.6373
11.000 1.3720 0.04232 0.03531 -0.0925 0.1499 0.6424
11.250 1.3725 0.04484 0.03772 -0.0907 0.1349 0.6476
11.500 1.3742 0.04726 0.04015 -0.0889 0.1222 0.6531
11.750 1.3773 0.04976 0.04270 -0.0876 0.1107 0.6601
12.000 1.3820 0.05221 0.04525 -0.0862 0.1006 0.6665
12.250 1.3899 0.05469 0.04768 -0.0852 0.0915 0.6750
12.500 1.3951 0.05710 0.05015 -0.0841 0.0838 0.6826
12.750 1.4033 0.05981 0.05300 -0.0832 0.0765 0.6922
13.000 1.4198 0.06214 0.05518 -0.0825 0.0687 0.7033
13.250 1.4176 0.06524 0.05868 -0.0814 0.0646 0.7122
13.500 1.4211 0.06798 0.06150 -0.0809 0.0599 0.7242
13.750 1.4300 0.07125 0.06495 -0.0802 0.0553 0.7384
14.000 1.4262 0.07480 0.06883 -0.0797 0.0521 0.7523
14.250 1.4267 0.07783 0.07200 -0.0794 0.0490 0.7707
14.500 1.4342 0.08162 0.07600 -0.0787 0.0459 0.7986
14.750 1.4201 0.08588 0.08073 -0.0784 0.0447 0.8343
15.000 1.4054 0.09004 0.08529 -0.0784 0.0436 1.0000
15.250 1.3954 0.09545 0.09094 -0.0804 0.0421 1.0000
15.500 1.3882 0.10046 0.09609 -0.0823 0.0406 1.0000
15.750 1.3796 0.10561 0.10137 -0.0844 0.0394 1.0000
16.000 1.3752 0.11049 0.10632 -0.0862 0.0382 1.0000
16.250 1.3642 0.11663 0.11263 -0.0887 0.0377 1.0000
16.500 1.3454 0.12383 0.12008 -0.0925 0.0377 1.0000
16.750 1.3189 0.13251 0.12909 -0.0981 0.0381 1.0000
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