NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NREL's S818 Airfoil (s818-nr) Reynolds number: 200,000 Max Cl/Cd: 57.7 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s818-nr-200000.txt Download as CSV file: xf-s818-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S818 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3338 0.11505 0.11023 -0.0240 1.0000 0.3571
-10.500 -0.3215 0.11402 0.10919 -0.0230 1.0000 0.3599
-10.250 -0.3702 0.11393 0.10910 -0.0216 1.0000 0.3688
-10.000 -0.3504 0.11181 0.10697 -0.0209 1.0000 0.3693
-9.750 -0.3333 0.11014 0.10528 -0.0199 1.0000 0.3700
-9.500 -0.3186 0.10883 0.10396 -0.0188 1.0000 0.3708
-9.250 -0.3060 0.10782 0.10295 -0.0174 1.0000 0.3720
-9.000 -0.2769 0.10590 0.10099 -0.0202 0.9975 0.3735
-8.750 -0.3193 0.10704 0.10205 -0.0260 0.9904 0.3843
-8.500 -0.2788 0.10361 0.09857 -0.0296 0.9866 0.3845
-8.250 -0.2367 0.10041 0.09531 -0.0335 0.9835 0.3849
-8.000 -0.1966 0.09759 0.09244 -0.0376 0.9812 0.3853
-7.750 -0.1639 0.09509 0.08990 -0.0403 0.9757 0.3857
-7.500 -0.1279 0.09267 0.08745 -0.0438 0.9717 0.3862
-7.250 -0.0894 0.09035 0.08508 -0.0480 0.9689 0.3870
-7.000 -0.0589 0.08827 0.08299 -0.0505 0.9627 0.3879
-6.750 -0.0255 0.08612 0.08081 -0.0540 0.9575 0.3889
-6.500 0.0102 0.08393 0.07859 -0.0583 0.9543 0.3901
-6.250 0.0323 0.08213 0.07679 -0.0594 0.9439 0.3915
-6.000 0.0636 0.08006 0.07470 -0.0631 0.9391 0.3934
-5.750 0.0085 0.08044 0.07505 -0.0619 0.9143 0.4008
-5.500 0.0359 0.07808 0.07269 -0.0627 0.9009 0.4010
-5.250 0.0660 0.07573 0.07033 -0.0638 0.8870 0.4014
-5.000 0.1024 0.07326 0.06783 -0.0665 0.8741 0.4017
-4.750 0.1492 0.07050 0.06501 -0.0716 0.8610 0.4022
-4.500 0.2125 0.06735 0.06174 -0.0807 0.8442 0.4027
-4.250 0.3084 0.06346 0.05762 -0.0976 0.8185 0.4035
-4.000 0.3799 0.06084 0.05464 -0.1092 0.7746 0.4044
-3.750 0.4097 0.05980 0.05330 -0.1113 0.7349 0.4055
-3.500 0.4279 0.05913 0.05241 -0.1109 0.7057 0.4067
-3.250 0.3535 0.06152 0.05471 -0.1053 0.6897 0.4169
-3.000 0.3779 0.06000 0.05305 -0.1050 0.6695 0.4172
-2.750 0.4017 0.05867 0.05161 -0.1047 0.6520 0.4175
-2.500 0.4251 0.05749 0.05032 -0.1043 0.6369 0.4178
-2.250 0.4476 0.05644 0.04917 -0.1039 0.6239 0.4182
-2.000 0.4689 0.05550 0.04817 -0.1034 0.6116 0.4187
-1.750 0.4900 0.05463 0.04725 -0.1029 0.6007 0.4193
-1.500 0.5113 0.05387 0.04639 -0.1026 0.5915 0.4200
-1.250 0.5296 0.05314 0.04568 -0.1017 0.5820 0.4209
-1.000 0.5490 0.05249 0.04494 -0.1014 0.5745 0.4220
-0.750 0.5648 0.05188 0.04435 -0.1004 0.5667 0.4234
-0.500 0.5798 0.05129 0.04374 -0.0996 0.5603 0.4253
-0.250 0.5912 0.05081 0.04321 -0.0987 0.5550 0.4283
0.000 0.5350 0.05031 0.04280 -0.0920 0.5519 0.4345
0.250 0.5604 0.04938 0.04187 -0.0920 0.5460 0.4349
0.500 0.5876 0.04855 0.04098 -0.0924 0.5411 0.4355
0.750 0.6106 0.04785 0.04030 -0.0922 0.5365 0.4363
1.000 0.6314 0.04723 0.03974 -0.0915 0.5318 0.4372
1.250 0.6523 0.04668 0.03920 -0.0909 0.5275 0.4386
1.500 0.6719 0.04617 0.03867 -0.0905 0.5240 0.4405
1.750 0.6836 0.04577 0.03828 -0.0891 0.5206 0.4433
2.000 0.6354 0.04478 0.03737 -0.0852 0.5186 0.4514
2.250 0.6543 0.04413 0.03678 -0.0838 0.5147 0.4519
2.500 0.6752 0.04354 0.03623 -0.0829 0.5112 0.4526
2.750 0.6974 0.04298 0.03567 -0.0824 0.5083 0.4534
3.000 0.7218 0.04249 0.03516 -0.0827 0.5056 0.4544
3.250 0.7374 0.04203 0.03479 -0.0816 0.5030 0.4557
3.500 0.7504 0.04151 0.03437 -0.0804 0.5003 0.4571
3.750 0.7643 0.04093 0.03386 -0.0798 0.4976 0.4590
4.000 0.7792 0.04010 0.03307 -0.0803 0.4951 0.4604
4.250 0.8836 0.02393 0.01568 -0.1280 0.4920 0.4213
4.500 0.9153 0.02407 0.01582 -0.1291 0.4895 0.4228
4.750 0.9463 0.02427 0.01604 -0.1302 0.4871 0.4246
5.000 0.9724 0.02438 0.01627 -0.1303 0.4847 0.4266
5.250 1.0007 0.02449 0.01646 -0.1310 0.4822 0.4291
5.500 1.0313 0.02461 0.01659 -0.1322 0.4798 0.4318
5.750 1.0619 0.02470 0.01671 -0.1333 0.4773 0.4340
6.000 1.0907 0.02483 0.01692 -0.1337 0.4749 0.4357
6.250 1.1210 0.02510 0.01725 -0.1345 0.4728 0.4375
6.500 1.1532 0.02552 0.01771 -0.1356 0.4706 0.4396
6.750 1.1739 0.02577 0.01815 -0.1347 0.4677 0.4417
7.000 1.1975 0.02603 0.01854 -0.1343 0.4644 0.4440
7.250 1.2244 0.02625 0.01883 -0.1345 0.4612 0.4467
7.500 1.2550 0.02640 0.01898 -0.1354 0.4579 0.4495
7.750 1.2878 0.02637 0.01891 -0.1364 0.4526 0.4520
8.000 1.3010 0.02624 0.01898 -0.1338 0.4451 0.4539
8.250 1.3322 0.02593 0.01861 -0.1342 0.4382 0.4567
8.500 1.3519 0.02615 0.01896 -0.1330 0.4332 0.4596
8.750 1.3707 0.02625 0.01920 -0.1316 0.4279 0.4629
9.000 1.4007 0.02615 0.01901 -0.1320 0.4223 0.4667
9.250 1.4219 0.02621 0.01920 -0.1310 0.4169 0.4694
9.500 1.4347 0.02627 0.01946 -0.1284 0.4108 0.4719
9.750 1.4610 0.02612 0.01930 -0.1281 0.4048 0.4753
10.000 1.4744 0.02628 0.01960 -0.1257 0.3989 0.4785
10.250 1.4864 0.02629 0.01971 -0.1231 0.3923 0.4819
10.500 1.5088 0.02615 0.01951 -0.1221 0.3855 0.4854
10.750 1.5054 0.02637 0.02000 -0.1170 0.3790 0.4876
11.000 1.5164 0.02641 0.02010 -0.1142 0.3715 0.4907
11.250 1.5195 0.02678 0.02064 -0.1104 0.3637 0.4941
11.500 1.5259 0.02705 0.02095 -0.1072 0.3547 0.4982
11.750 1.5271 0.02765 0.02171 -0.1036 0.3446 0.5017
12.000 1.5290 0.02823 0.02243 -0.1002 0.3331 0.5048
12.250 1.5278 0.02911 0.02344 -0.0967 0.3185 0.5080
12.500 1.5240 0.03034 0.02476 -0.0933 0.2975 0.5115
12.750 1.5125 0.03223 0.02656 -0.0896 0.2690 0.5147
13.000 1.4909 0.03522 0.02936 -0.0859 0.2411 0.5171
13.250 1.4664 0.03902 0.03306 -0.0830 0.2171 0.5190
13.500 1.4410 0.04345 0.03744 -0.0809 0.1973 0.5206
13.750 1.4175 0.04826 0.04223 -0.0798 0.1792 0.5223
14.000 1.3945 0.05345 0.04740 -0.0793 0.1637 0.5241
14.250 1.3727 0.05886 0.05280 -0.0793 0.1506 0.5261
14.500 1.3534 0.06425 0.05818 -0.0798 0.1390 0.5284
14.750 1.3389 0.06931 0.06325 -0.0805 0.1282 0.5313
15.000 1.3259 0.07433 0.06825 -0.0813 0.1191 0.5345
15.250 1.3138 0.07931 0.07321 -0.0823 0.1110 0.5371
15.500 1.3082 0.08356 0.07753 -0.0831 0.1031 0.5405
15.750 1.2996 0.08816 0.08208 -0.0841 0.0966 0.5442
16.000 1.2996 0.09186 0.08586 -0.0851 0.0901 0.5495
16.250 1.2960 0.09592 0.08987 -0.0862 0.0846 0.5540
16.500 1.2979 0.09932 0.09339 -0.0871 0.0794 0.5589
16.750 1.2985 0.10295 0.09704 -0.0882 0.0749 0.5649
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