NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S818 Airfoil (s818-nr) Reynolds number: 500,000 Max Cl/Cd: 83.4 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s818-nr-500000.txt Download as CSV file: xf-s818-nr-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7238 0.09180 0.08736 -0.0394 1.0000 0.0888
-14.250 -0.7264 0.08918 0.08484 -0.0393 1.0000 0.1004
-14.000 -0.7386 0.08548 0.08129 -0.0394 1.0000 0.1177
-13.750 -0.7608 0.08076 0.07677 -0.0396 1.0000 0.1433
-13.500 -0.7962 0.07482 0.07105 -0.0397 1.0000 0.1737
-13.250 -0.8390 0.06851 0.06499 -0.0397 1.0000 0.2027
-12.000 -1.0206 0.03910 0.03572 -0.0454 0.9923 0.2883
-11.750 -1.0705 0.03033 0.02668 -0.0521 0.9811 0.2855
-11.500 -0.9052 0.04288 0.03952 -0.0500 0.9882 0.3116
-11.250 -0.9109 0.03798 0.03453 -0.0555 0.9828 0.3161
-11.000 -0.8448 0.04074 0.03726 -0.0583 0.9822 0.3214
-10.750 -0.8166 0.04007 0.03654 -0.0607 0.9788 0.3240
-10.500 -0.8431 0.03372 0.03009 -0.0653 0.9696 0.3268
-10.250 -0.8425 0.03158 0.02789 -0.0662 0.9607 0.3290
-10.000 -0.8171 0.02970 0.02592 -0.0714 0.9560 0.3325
-9.750 -0.7667 0.03048 0.02665 -0.0752 0.9549 0.3358
-9.500 -0.7129 0.03210 0.02827 -0.0772 0.9544 0.3382
-6.750 -0.4177 0.02521 0.02101 -0.0890 0.8846 0.3494
-6.500 -0.3967 0.02022 0.01559 -0.0972 0.8724 0.3510
-6.250 -0.3490 0.01892 0.01414 -0.1028 0.8647 0.3514
-6.000 -0.2981 0.01795 0.01301 -0.1087 0.8510 0.3517
-5.750 -0.2354 0.01720 0.01207 -0.1167 0.8336 0.3520
-5.500 -0.1830 0.01671 0.01136 -0.1226 0.8071 0.3522
-5.250 -0.1493 0.01640 0.01082 -0.1245 0.7766 0.3525
-5.000 -0.1245 0.01581 0.01000 -0.1250 0.7479 0.3531
-4.750 -0.1014 0.01535 0.00937 -0.1248 0.7223 0.3537
-4.500 -0.0782 0.01506 0.00893 -0.1244 0.6992 0.3541
-4.250 -0.0547 0.01485 0.00859 -0.1240 0.6786 0.3546
-4.000 -0.0306 0.01468 0.00831 -0.1237 0.6596 0.3550
-3.750 -0.0061 0.01453 0.00806 -0.1234 0.6419 0.3555
-3.500 0.0187 0.01442 0.00784 -0.1232 0.6255 0.3559
-3.250 0.0441 0.01431 0.00764 -0.1231 0.6100 0.3564
-3.000 0.0701 0.01421 0.00747 -0.1230 0.5957 0.3568
-2.750 0.0963 0.01414 0.00732 -0.1230 0.5826 0.3574
-2.500 0.1225 0.01409 0.00720 -0.1230 0.5704 0.3580
-2.250 0.1490 0.01406 0.00710 -0.1230 0.5588 0.3586
-2.000 0.1763 0.01401 0.00699 -0.1231 0.5483 0.3593
-1.750 0.2032 0.01398 0.00689 -0.1232 0.5384 0.3600
-1.500 0.2310 0.01390 0.00677 -0.1235 0.5289 0.3607
-1.250 0.2586 0.01388 0.00666 -0.1237 0.5205 0.3613
-1.000 0.2868 0.01381 0.00656 -0.1241 0.5126 0.3621
-0.750 0.3147 0.01381 0.00648 -0.1244 0.5055 0.3628
-0.500 0.3435 0.01375 0.00640 -0.1248 0.4992 0.3636
-0.250 0.3719 0.01372 0.00632 -0.1252 0.4930 0.3644
0.000 0.4006 0.01376 0.00628 -0.1256 0.4874 0.3652
0.250 0.4295 0.01371 0.00623 -0.1260 0.4825 0.3659
0.500 0.4582 0.01371 0.00620 -0.1264 0.4776 0.3666
0.750 0.4871 0.01377 0.00620 -0.1268 0.4731 0.3673
1.000 0.5166 0.01383 0.00622 -0.1273 0.4691 0.3678
1.250 0.5459 0.01372 0.00612 -0.1279 0.4654 0.3688
1.500 0.5751 0.01361 0.00602 -0.1284 0.4616 0.3702
1.750 0.6038 0.01362 0.00603 -0.1288 0.4580 0.3713
2.000 0.6338 0.01374 0.00612 -0.1294 0.4543 0.3724
2.250 0.6628 0.01377 0.00620 -0.1298 0.4516 0.3734
2.500 0.6914 0.01381 0.00628 -0.1301 0.4489 0.3745
2.750 0.7203 0.01386 0.00636 -0.1304 0.4462 0.3756
3.000 0.7493 0.01393 0.00645 -0.1308 0.4437 0.3768
3.250 0.7788 0.01403 0.00654 -0.1312 0.4412 0.3781
3.500 0.8095 0.01417 0.00667 -0.1320 0.4387 0.3794
3.750 0.8416 0.01436 0.00684 -0.1330 0.4363 0.3808
4.000 0.8702 0.01443 0.00695 -0.1333 0.4346 0.3820
4.250 0.8991 0.01452 0.00708 -0.1336 0.4327 0.3831
4.500 0.9279 0.01463 0.00721 -0.1339 0.4306 0.3840
4.750 0.9573 0.01461 0.00725 -0.1344 0.4284 0.3861
5.000 0.9866 0.01468 0.00738 -0.1349 0.4264 0.3878
5.250 1.0160 0.01482 0.00756 -0.1353 0.4247 0.3894
5.500 1.0462 0.01500 0.00777 -0.1359 0.4229 0.3912
5.750 1.0785 0.01525 0.00804 -0.1369 0.4209 0.3931
6.000 1.1100 0.01549 0.00832 -0.1378 0.4192 0.3951
6.250 1.1368 0.01560 0.00850 -0.1377 0.4176 0.3969
6.500 1.1628 0.01570 0.00867 -0.1375 0.4153 0.3985
6.750 1.1875 0.01578 0.00880 -0.1369 0.4120 0.3998
7.000 1.2073 0.01573 0.00875 -0.1355 0.4064 0.4017
7.250 1.2266 0.01576 0.00884 -0.1340 0.4002 0.4038
7.500 1.2450 0.01577 0.00895 -0.1322 0.3956 0.4057
7.750 1.2680 0.01588 0.00912 -0.1314 0.3921 0.4077
8.000 1.2923 0.01608 0.00932 -0.1309 0.3881 0.4098
8.250 1.3147 0.01625 0.00956 -0.1300 0.3840 0.4119
8.500 1.3351 0.01637 0.00977 -0.1287 0.3799 0.4140
8.750 1.3565 0.01652 0.00997 -0.1277 0.3758 0.4158
9.000 1.3783 0.01672 0.01018 -0.1268 0.3710 0.4181
9.250 1.3990 0.01687 0.01045 -0.1256 0.3663 0.4208
9.500 1.4187 0.01701 0.01071 -0.1243 0.3606 0.4232
9.750 1.4373 0.01728 0.01100 -0.1229 0.3545 0.4258
10.000 1.4570 0.01750 0.01132 -0.1216 0.3481 0.4287
10.250 1.4750 0.01777 0.01164 -0.1201 0.3400 0.4313
10.500 1.4937 0.01807 0.01199 -0.1188 0.3311 0.4338
10.750 1.5096 0.01844 0.01242 -0.1171 0.3186 0.4371
11.000 1.5235 0.01896 0.01295 -0.1152 0.2984 0.4399
11.250 1.5245 0.02009 0.01392 -0.1116 0.2633 0.4423
11.500 1.5153 0.02193 0.01554 -0.1070 0.2275 0.4443
11.750 1.5069 0.02391 0.01737 -0.1029 0.1983 0.4464
12.000 1.4997 0.02598 0.01933 -0.0993 0.1735 0.4484
12.250 1.4914 0.02828 0.02153 -0.0961 0.1534 0.4501
12.500 1.4849 0.03067 0.02390 -0.0935 0.1365 0.4528
12.750 1.4783 0.03327 0.02650 -0.0914 0.1226 0.4552
13.000 1.4718 0.03610 0.02933 -0.0897 0.1108 0.4577
13.250 1.4665 0.03902 0.03230 -0.0884 0.1012 0.4603
13.500 1.4599 0.04227 0.03557 -0.0874 0.0933 0.4630
13.750 1.4524 0.04582 0.03915 -0.0868 0.0862 0.4655
14.000 1.4470 0.04934 0.04273 -0.0865 0.0803 0.4683
14.250 1.4394 0.05327 0.04673 -0.0865 0.0750 0.4713
14.500 1.4327 0.05723 0.05077 -0.0866 0.0705 0.4743
14.750 1.4272 0.06114 0.05476 -0.0869 0.0663 0.4776
15.000 1.4174 0.06567 0.05933 -0.0874 0.0624 0.4805
15.250 1.4133 0.06958 0.06331 -0.0879 0.0591 0.4836
15.500 1.4087 0.07371 0.06753 -0.0887 0.0558 0.4871
15.750 1.4006 0.07834 0.07222 -0.0896 0.0527 0.4903
16.000 1.3984 0.08225 0.07622 -0.0904 0.0501 0.4943
16.250 1.3964 0.08616 0.08019 -0.0913 0.0475 0.4985
16.500 1.3914 0.09054 0.08461 -0.0924 0.0451 0.5021
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