NREL's S825 Airfoil (s825-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S825 Airfoil (s825-nr) Reynolds number: 100,000 Max Cl/Cd: 52.76 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s825-nr-100000-n5.txt Download as CSV file: xf-s825-nr-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5176 0.10101 0.09569 -0.0562 1.0000 0.0184
-12.500 -0.5365 0.09452 0.08913 -0.0589 1.0000 0.0182
-12.250 -0.5611 0.08768 0.08216 -0.0618 1.0000 0.0182
-12.000 -0.5781 0.08267 0.07705 -0.0634 1.0000 0.0180
-11.750 -0.5969 0.07782 0.07207 -0.0647 1.0000 0.0179
-11.500 -0.6129 0.07358 0.06771 -0.0655 1.0000 0.0178
-11.250 -0.6299 0.06947 0.06343 -0.0660 1.0000 0.0179
-11.000 -0.6427 0.06600 0.05982 -0.0659 1.0000 0.0179
-10.750 -0.6559 0.06258 0.05624 -0.0654 1.0000 0.0180
-10.500 -0.6651 0.05971 0.05320 -0.0644 1.0000 0.0180
-10.250 -0.6728 0.05702 0.05034 -0.0631 1.0000 0.0182
-10.000 -0.6771 0.05474 0.04791 -0.0613 1.0000 0.0183
-9.750 -0.6794 0.05260 0.04557 -0.0591 1.0000 0.0186
-9.500 -0.6786 0.05084 0.04360 -0.0566 1.0000 0.0189
-9.250 -0.6748 0.04941 0.04208 -0.0539 1.0000 0.0193
-9.000 -0.6715 0.04830 0.04096 -0.0510 1.0000 0.0197
-8.750 -0.6709 0.04733 0.03999 -0.0480 1.0000 0.0202
-8.500 -0.6699 0.04649 0.03914 -0.0449 1.0000 0.0209
-8.250 -0.6561 0.04565 0.03824 -0.0437 0.9983 0.0226
-8.000 -0.6246 0.04524 0.03770 -0.0435 0.9945 0.0252
-7.750 -0.5938 0.04522 0.03775 -0.0432 0.9903 0.0275
-7.500 -0.5486 0.04699 0.03950 -0.0411 0.9879 0.0325
-7.250 -0.5126 0.04771 0.04029 -0.0414 0.9839 0.0384
-7.000 -0.4890 0.04767 0.04032 -0.0414 0.9769 0.0452
-6.750 -0.4632 0.04693 0.03964 -0.0436 0.9707 0.0545
-6.500 -0.4470 0.04546 0.03821 -0.0453 0.9611 0.0647
-6.250 -0.4306 0.04313 0.03600 -0.0489 0.9516 0.0802
-6.000 -0.4062 0.03947 0.03246 -0.0565 0.9436 0.1055
-5.750 -0.3707 0.04441 0.03887 -0.0497 0.9366 0.2283
-5.500 -0.3234 0.03013 0.02372 -0.0843 0.9266 0.3507
-5.250 -0.2808 0.03027 0.02351 -0.0887 0.9197 0.3745
-4.750 -0.2304 0.03599 0.02924 -0.0781 0.9040 0.3917
-4.500 -0.2065 0.03701 0.03017 -0.0755 0.8939 0.3985
-4.250 -0.1716 0.03698 0.03001 -0.0768 0.8879 0.4057
-4.000 -0.1493 0.03815 0.03115 -0.0729 0.8783 0.4098
-3.500 -0.0707 0.03381 0.02634 -0.0854 0.8631 0.4186
-3.250 -0.0375 0.03265 0.02504 -0.0877 0.8549 0.4190
-3.000 0.0000 0.03129 0.02352 -0.0912 0.8475 0.4193
-2.750 0.0350 0.03008 0.02217 -0.0942 0.8382 0.4196
-2.500 0.0755 0.02890 0.02084 -0.0978 0.8313 0.4200
-2.250 0.1109 0.02793 0.01975 -0.1005 0.8206 0.4205
-2.000 0.1527 0.02694 0.01863 -0.1041 0.8128 0.4212
-1.750 0.1922 0.02609 0.01766 -0.1073 0.8024 0.4219
-1.500 0.2324 0.02531 0.01676 -0.1105 0.7915 0.4227
-1.250 0.2770 0.02455 0.01587 -0.1145 0.7814 0.4237
-1.000 0.3222 0.02386 0.01505 -0.1187 0.7700 0.4249
-0.750 0.3634 0.02328 0.01434 -0.1220 0.7567 0.4264
-0.500 0.4044 0.02273 0.01365 -0.1254 0.7432 0.4283
-0.250 0.4462 0.02214 0.01290 -0.1292 0.7300 0.4307
0.000 0.4888 0.02152 0.01206 -0.1333 0.7166 0.4330
0.250 0.5235 0.02134 0.01182 -0.1348 0.7033 0.4340
0.500 0.5569 0.02123 0.01165 -0.1361 0.6905 0.4349
0.750 0.5887 0.02115 0.01153 -0.1371 0.6781 0.4360
1.000 0.6191 0.02110 0.01145 -0.1379 0.6661 0.4371
1.250 0.6500 0.02105 0.01137 -0.1388 0.6551 0.4385
1.500 0.6820 0.02101 0.01127 -0.1399 0.6450 0.4401
1.750 0.7118 0.02098 0.01123 -0.1407 0.6342 0.4418
2.000 0.7424 0.02096 0.01117 -0.1416 0.6244 0.4439
2.500 0.8048 0.02095 0.01107 -0.1438 0.6068 0.4489
2.750 0.8339 0.02108 0.01121 -0.1441 0.5993 0.4504
3.000 0.8604 0.02122 0.01146 -0.1441 0.5905 0.4521
3.250 0.8900 0.02136 0.01161 -0.1446 0.5838 0.4540
3.500 0.9171 0.02150 0.01185 -0.1447 0.5760 0.4560
4.000 0.9750 0.02179 0.01222 -0.1457 0.5621 0.4609
4.250 1.0052 0.02193 0.01236 -0.1465 0.5557 0.4637
4.500 1.0317 0.02214 0.01270 -0.1464 0.5492 0.4654
4.750 1.0579 0.02236 0.01305 -0.1462 0.5420 0.4673
5.000 1.0843 0.02258 0.01338 -0.1460 0.5346 0.4697
5.250 1.1096 0.02279 0.01368 -0.1457 0.5257 0.4725
5.500 1.1344 0.02299 0.01399 -0.1453 0.5159 0.4759
5.750 1.1608 0.02316 0.01416 -0.1451 0.5059 0.4795
6.000 1.1824 0.02337 0.01454 -0.1440 0.4950 0.4817
6.250 1.2046 0.02360 0.01492 -0.1430 0.4844 0.4843
6.500 1.2279 0.02382 0.01524 -0.1422 0.4739 0.4874
6.750 1.2499 0.02403 0.01557 -0.1412 0.4623 0.4907
7.000 1.2707 0.02428 0.01594 -0.1401 0.4498 0.4942
7.250 1.2900 0.02454 0.01636 -0.1386 0.4369 0.4967
7.500 1.3083 0.02482 0.01679 -0.1369 0.4228 0.4996
7.750 1.3253 0.02512 0.01725 -0.1350 0.4070 0.5032
8.000 1.3408 0.02547 0.01770 -0.1329 0.3891 0.5073
8.250 1.3536 0.02588 0.01818 -0.1304 0.3689 0.5109
8.500 1.3627 0.02634 0.01879 -0.1273 0.3439 0.5140
8.750 1.3695 0.02700 0.01944 -0.1239 0.3120 0.5175
9.000 1.3725 0.02800 0.02029 -0.1202 0.2738 0.5212
9.500 1.3707 0.03098 0.02297 -0.1127 0.2098 0.5275
9.750 1.3699 0.03268 0.02462 -0.1094 0.1852 0.5305
10.000 1.3683 0.03455 0.02643 -0.1062 0.1648 0.5339
10.250 1.3675 0.03649 0.02836 -0.1034 0.1477 0.5378
10.500 1.3663 0.03856 0.03044 -0.1009 0.1331 0.5415
10.750 1.3642 0.04081 0.03274 -0.0986 0.1207 0.5449
11.000 1.3629 0.04315 0.03515 -0.0967 0.1096 0.5490
11.250 1.3622 0.04562 0.03769 -0.0951 0.1000 0.5536
11.500 1.3594 0.04838 0.04051 -0.0937 0.0920 0.5574
11.750 1.3577 0.05119 0.04343 -0.0926 0.0843 0.5616
12.000 1.3559 0.05417 0.04650 -0.0918 0.0780 0.5663
12.250 1.3543 0.05728 0.04973 -0.0912 0.0719 0.5711
12.500 1.3518 0.06058 0.05312 -0.0908 0.0669 0.5754
12.750 1.3517 0.06375 0.05645 -0.0906 0.0617 0.5809
13.000 1.3474 0.06750 0.06024 -0.0906 0.0579 0.5863
13.250 1.3484 0.07072 0.06366 -0.0906 0.0535 0.5919
13.500 1.3475 0.07428 0.06735 -0.0909 0.0498 0.5986
13.750 1.3434 0.07831 0.07144 -0.0914 0.0469 0.6043
14.000 1.3446 0.08174 0.07507 -0.0917 0.0436 0.6120
14.250 1.3439 0.08551 0.07901 -0.0923 0.0405 0.6196
14.500 1.3411 0.08963 0.08323 -0.0933 0.0383 0.6278
14.750 1.3397 0.09359 0.08733 -0.0941 0.0359 0.6367
15.000 1.3398 0.09748 0.09145 -0.0950 0.0334 0.6476
15.250 1.3377 0.10172 0.09586 -0.0963 0.0313 0.6597
15.500 1.3348 0.10614 0.10044 -0.0979 0.0298 0.6732
15.750 1.3328 0.11040 0.10487 -0.0992 0.0281 0.6901
16.000 1.3312 0.11477 0.10954 -0.1007 0.0264 0.7123
16.250 1.3280 0.11931 0.11434 -0.1025 0.0249 0.7439
16.500 1.3224 0.12341 0.11874 -0.1036 0.0239 0.8355
16.750 1.3178 0.12776 0.12317 -0.1058 0.0230 1.0000
17.000 1.3149 0.13261 0.12808 -0.1083 0.0220 1.0000
17.250 1.3100 0.13819 0.13391 -0.1113 0.0211 1.0000
17.500 1.3040 0.14404 0.13997 -0.1147 0.0202 1.0000
17.750 1.2978 0.15006 0.14615 -0.1184 0.0194 1.0000
18.000 1.2913 0.15623 0.15247 -0.1224 0.0188 1.0000
18.250 1.2849 0.16253 0.15888 -0.1267 0.0183 1.0000
18.500 1.2789 0.16883 0.16530 -0.1310 0.0178 1.0000
18.750 1.2732 0.17515 0.17170 -0.1354 0.0175 1.0000
19.000 1.2680 0.18141 0.17804 -0.1398 0.0171 1.0000
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