NREL's S814 Airfoil (s814-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S814 Airfoil (s814-nr) Reynolds number: 200,000 Max Cl/Cd: 58.29 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s814-nr-200000.txt Download as CSV file: xf-s814-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S814 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1186 0.10738 0.10210 -0.0371 0.9826 0.3172
-7.500 -0.0845 0.10509 0.09979 -0.0413 0.9802 0.3189
-7.250 -0.1278 0.10434 0.09897 -0.0469 0.9700 0.3289
-7.000 -0.0841 0.10073 0.09535 -0.0506 0.9678 0.3292
-6.750 -0.0475 0.09770 0.09232 -0.0530 0.9624 0.3297
-6.500 -0.0111 0.09490 0.08953 -0.0559 0.9571 0.3302
-6.250 0.0279 0.09226 0.08690 -0.0595 0.9538 0.3309
-6.000 0.0559 0.09011 0.08477 -0.0610 0.9445 0.3319
-5.750 0.0899 0.08780 0.08247 -0.0644 0.9391 0.3332
-5.500 0.0275 0.08884 0.08344 -0.0661 0.9142 0.3442
-5.250 0.0634 0.08543 0.08005 -0.0676 0.9047 0.3446
-5.000 0.1004 0.08241 0.07703 -0.0694 0.8931 0.3449
-4.750 0.1408 0.07949 0.07411 -0.0723 0.8797 0.3454
-4.500 0.1921 0.07637 0.07095 -0.0778 0.8671 0.3460
-4.250 0.2588 0.07292 0.06742 -0.0874 0.8530 0.3469
-4.000 0.3359 0.06940 0.06375 -0.1000 0.8313 0.3484
-3.750 0.3943 0.06696 0.06105 -0.1087 0.7974 0.3504
-3.500 0.3382 0.06815 0.06196 -0.1090 0.7661 0.3603
-3.250 0.3703 0.06609 0.05973 -0.1098 0.7424 0.3607
-3.000 0.3977 0.06452 0.05802 -0.1099 0.7221 0.3611
-2.750 0.4231 0.06318 0.05657 -0.1096 0.7046 0.3616
-2.500 0.4464 0.06202 0.05531 -0.1092 0.6891 0.3622
-2.250 0.4676 0.06102 0.05426 -0.1086 0.6749 0.3629
-2.000 0.4878 0.06012 0.05332 -0.1081 0.6631 0.3639
-1.750 0.5082 0.05933 0.05242 -0.1077 0.6531 0.3653
-1.500 0.4244 0.06090 0.05404 -0.1027 0.6466 0.3765
-1.250 0.4550 0.05899 0.05207 -0.1031 0.6380 0.3768
-1.000 0.4837 0.05748 0.05055 -0.1032 0.6297 0.3772
-0.750 0.5096 0.05623 0.04928 -0.1030 0.6223 0.3776
-0.500 0.5364 0.05516 0.04818 -0.1031 0.6158 0.3782
-0.250 0.5591 0.05422 0.04728 -0.1026 0.6089 0.3789
0.000 0.5817 0.05337 0.04639 -0.1023 0.6031 0.3798
0.250 0.6022 0.05263 0.04567 -0.1018 0.5974 0.3810
0.500 0.6193 0.05193 0.04502 -0.1010 0.5919 0.3824
0.750 0.6355 0.05125 0.04434 -0.1004 0.5873 0.3845
1.000 0.6457 0.05065 0.04370 -0.0998 0.5836 0.3885
1.250 0.5953 0.04969 0.04283 -0.0944 0.5806 0.3944
1.500 0.6180 0.04887 0.04208 -0.0936 0.5761 0.3951
1.750 0.6406 0.04809 0.04134 -0.0931 0.5721 0.3958
2.000 0.6648 0.04739 0.04063 -0.0929 0.5684 0.3969
2.250 0.6836 0.04681 0.04007 -0.0923 0.5648 0.3981
2.500 0.6949 0.04632 0.03969 -0.0905 0.5610 0.3999
2.750 0.7050 0.04576 0.03920 -0.0891 0.5575 0.4024
3.000 0.6962 0.02374 0.01587 -0.1299 0.5555 0.3771
3.250 0.7254 0.02364 0.01582 -0.1304 0.5524 0.3784
3.500 0.7565 0.02374 0.01594 -0.1311 0.5494 0.3798
3.750 0.7817 0.02385 0.01617 -0.1308 0.5458 0.3814
4.000 0.8070 0.02395 0.01640 -0.1305 0.5421 0.3831
4.250 0.8353 0.02397 0.01647 -0.1309 0.5384 0.3853
4.500 0.8678 0.02384 0.01631 -0.1322 0.5347 0.3882
4.750 0.9059 0.02372 0.01603 -0.1349 0.5313 0.3913
5.000 0.9316 0.02358 0.01596 -0.1351 0.5272 0.3936
5.250 0.9565 0.02358 0.01611 -0.1347 0.5229 0.3953
5.500 0.9845 0.02364 0.01625 -0.1347 0.5187 0.3971
5.750 1.0177 0.02375 0.01633 -0.1357 0.5145 0.3994
6.000 1.0389 0.02383 0.01658 -0.1346 0.5092 0.4016
6.250 1.0649 0.02378 0.01658 -0.1344 0.5032 0.4045
6.500 1.1009 0.02366 0.01630 -0.1360 0.4976 0.4080
6.750 1.1224 0.02362 0.01638 -0.1350 0.4910 0.4107
7.000 1.1465 0.02352 0.01639 -0.1342 0.4842 0.4130
7.250 1.1749 0.02355 0.01644 -0.1341 0.4780 0.4158
7.500 1.1930 0.02358 0.01663 -0.1323 0.4709 0.4188
7.750 1.2226 0.02347 0.01647 -0.1325 0.4642 0.4226
8.000 1.2437 0.02350 0.01655 -0.1314 0.4569 0.4260
8.250 1.2660 0.02330 0.01643 -0.1303 0.4489 0.4287
8.500 1.2850 0.02329 0.01653 -0.1286 0.4411 0.4313
8.750 1.3020 0.02323 0.01656 -0.1265 0.4323 0.4341
9.000 1.3188 0.02323 0.01663 -0.1245 0.4235 0.4375
9.250 1.3336 0.02318 0.01661 -0.1221 0.4140 0.4411
9.500 1.3429 0.02321 0.01672 -0.1188 0.4042 0.4441
9.750 1.3540 0.02323 0.01678 -0.1158 0.3940 0.4468
10.000 1.3592 0.02350 0.01724 -0.1121 0.3812 0.4496
10.250 1.3662 0.02384 0.01768 -0.1088 0.3665 0.4530
10.500 1.3719 0.02430 0.01816 -0.1054 0.3480 0.4567
10.750 1.3747 0.02501 0.01881 -0.1020 0.3233 0.4601
11.000 1.3699 0.02612 0.01980 -0.0978 0.2938 0.4625
11.250 1.3593 0.02780 0.02135 -0.0935 0.2660 0.4645
11.500 1.3487 0.02982 0.02328 -0.0897 0.2401 0.4666
11.750 1.3362 0.03226 0.02562 -0.0864 0.2177 0.4688
12.000 1.3258 0.03488 0.02818 -0.0838 0.1969 0.4713
12.250 1.3150 0.03782 0.03105 -0.0818 0.1784 0.4738
12.500 1.3048 0.04103 0.03418 -0.0803 0.1623 0.4764
12.750 1.2950 0.04442 0.03754 -0.0793 0.1482 0.4787
13.000 1.2854 0.04797 0.04110 -0.0786 0.1362 0.4807
13.250 1.2752 0.05177 0.04488 -0.0781 0.1257 0.4829
13.500 1.2703 0.05520 0.04836 -0.0779 0.1156 0.4857
13.750 1.2641 0.05891 0.05207 -0.0779 0.1073 0.4888
14.000 1.2585 0.06267 0.05581 -0.0781 0.0998 0.4921
14.250 1.2566 0.06616 0.05931 -0.0784 0.0929 0.4955
14.500 1.2530 0.06981 0.06299 -0.0788 0.0870 0.4983
14.750 1.2524 0.07318 0.06642 -0.0792 0.0815 0.5016
15.000 1.2531 0.07653 0.06981 -0.0797 0.0766 0.5055
15.250 1.2525 0.07997 0.07320 -0.0801 0.0724 0.5095
15.500 1.2572 0.08299 0.07633 -0.0807 0.0683 0.5136
15.750 1.2594 0.08622 0.07962 -0.0814 0.0649 0.5175
16.000 1.2635 0.08908 0.08245 -0.0817 0.0615 0.5223
16.250 1.2686 0.09211 0.08558 -0.0824 0.0586 0.5279
16.500 1.2735 0.09512 0.08867 -0.0832 0.0560 0.5327
16.750 1.2811 0.09743 0.09091 -0.0834 0.0533 0.5384
17.000 1.2873 0.10037 0.09398 -0.0841 0.0513 0.5448
17.250 1.2929 0.10335 0.09710 -0.0850 0.0492 0.5502
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