NREL's S819 Airfoil (s819-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S819 Airfoil (s819-nr) Reynolds number: 200,000 Max Cl/Cd: 55.62 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s819-nr-200000.txt Download as CSV file: xf-s819-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S819 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8651 0.09469 0.08913 -0.0604 1.0000 0.0341
-15.500 -0.8866 0.09131 0.08559 -0.0615 1.0000 0.0343
-15.250 -0.9081 0.08826 0.08238 -0.0623 1.0000 0.0344
-15.000 -0.9273 0.08543 0.07940 -0.0627 1.0000 0.0345
-14.750 -0.9506 0.08314 0.07694 -0.0628 1.0000 0.0347
-14.500 -0.8891 0.07661 0.07053 -0.0620 1.0000 0.0380
-14.250 -0.8859 0.07401 0.06787 -0.0618 1.0000 0.0393
-14.000 -0.8935 0.07150 0.06524 -0.0618 1.0000 0.0408
-13.750 -0.9045 0.06930 0.06289 -0.0616 1.0000 0.0416
-13.500 -0.9210 0.06735 0.06079 -0.0610 1.0000 0.0423
-13.250 -0.9483 0.06598 0.05925 -0.0598 1.0000 0.0429
-13.000 -0.9699 0.06491 0.05804 -0.0579 1.0000 0.0432
-12.750 -1.0019 0.06452 0.05752 -0.0542 1.0000 0.0435
-12.500 -1.0264 0.06414 0.05703 -0.0496 1.0000 0.0436
-12.250 -1.0511 0.06406 0.05678 -0.0451 1.0000 0.0438
-12.000 -0.8442 0.05261 0.04591 -0.0563 1.0000 0.0741
-11.750 -0.7932 0.05228 0.04571 -0.0539 1.0000 0.0840
-11.500 -0.7705 0.05176 0.04518 -0.0522 1.0000 0.0873
-11.250 -0.7600 0.05060 0.04395 -0.0510 1.0000 0.0892
-11.000 -0.7383 0.05024 0.04354 -0.0493 1.0000 0.0899
-10.750 -0.6237 0.05927 0.05295 -0.0411 1.0000 0.0855
-10.500 -0.6099 0.05799 0.05146 -0.0406 1.0000 0.0787
-10.250 -0.5775 0.05894 0.05228 -0.0387 1.0000 0.0664
-10.000 -0.5443 0.06025 0.05350 -0.0364 1.0000 0.0550
-9.750 -0.5052 0.06314 0.05643 -0.0328 1.0000 0.0459
-9.500 -0.4832 0.06382 0.05716 -0.0306 1.0000 0.0412
-9.250 -0.4671 0.06358 0.05683 -0.0289 1.0000 0.0365
-9.000 -0.4634 0.06135 0.05451 -0.0287 1.0000 0.0353
-8.750 -0.4421 0.06326 0.05663 -0.0251 1.0000 0.0326
-8.500 -0.4318 0.06298 0.05640 -0.0233 1.0000 0.0310
-8.250 -0.4228 0.06241 0.05584 -0.0215 1.0000 0.0294
-8.000 -0.4187 0.06109 0.05449 -0.0201 1.0000 0.0285
-7.750 -0.4167 0.05970 0.05310 -0.0186 1.0000 0.0280
-7.500 -0.4199 0.05850 0.05197 -0.0164 1.0000 0.0277
-7.250 -0.4340 0.05625 0.04973 -0.0142 1.0000 0.0276
-7.000 -0.4550 0.05379 0.04729 -0.0114 1.0000 0.0274
-6.750 -0.4816 0.05154 0.04504 -0.0077 1.0000 0.0275
-6.500 -0.4838 0.04602 0.03940 -0.0136 0.9933 0.0273
-6.250 -0.4852 0.03926 0.03243 -0.0218 0.9828 0.0272
-6.000 -0.4866 0.03323 0.02616 -0.0289 0.9678 0.0269
-5.750 -0.4845 0.02823 0.02089 -0.0351 0.9500 0.0268
-5.500 -0.4625 0.02484 0.01720 -0.0411 0.9367 0.0269
-5.250 -0.4269 0.02307 0.01519 -0.0456 0.9295 0.0275
-5.000 -0.4002 0.02155 0.01342 -0.0476 0.9178 0.0300
-4.750 -0.3571 0.02047 0.01215 -0.0516 0.9136 0.0318
-4.500 -0.3274 0.01975 0.01130 -0.0526 0.9018 0.0334
-4.250 -0.2933 0.01905 0.01051 -0.0542 0.8918 0.0396
-4.000 -0.2732 0.01583 0.00810 -0.0571 0.8801 0.2851
-3.750 -0.2343 0.01598 0.00836 -0.0597 0.8692 0.3306
-3.500 -0.1978 0.01707 0.00952 -0.0610 0.8555 0.3536
-3.250 -0.1598 0.01902 0.01178 -0.0615 0.8412 0.3714
-3.000 -0.1269 0.01922 0.01189 -0.0623 0.8260 0.3765
-2.750 -0.0976 0.01878 0.01125 -0.0631 0.8101 0.3781
-2.500 -0.0694 0.01844 0.01070 -0.0636 0.7942 0.3797
-2.250 -0.0417 0.01805 0.01022 -0.0638 0.7787 0.3812
-2.000 -0.0141 0.01782 0.00994 -0.0639 0.7637 0.3826
-1.750 0.0133 0.01766 0.00972 -0.0639 0.7491 0.3839
-1.500 0.0407 0.01752 0.00951 -0.0640 0.7353 0.3854
-1.250 0.0681 0.01738 0.00928 -0.0641 0.7219 0.3871
-1.000 0.0947 0.01723 0.00906 -0.0640 0.7079 0.3890
-0.750 0.1213 0.01708 0.00883 -0.0641 0.6945 0.3911
-0.500 0.1483 0.01694 0.00858 -0.0642 0.6818 0.3933
-0.250 0.1758 0.01684 0.00833 -0.0644 0.6697 0.3954
0.000 0.2029 0.01666 0.00813 -0.0644 0.6580 0.3974
0.250 0.2292 0.01658 0.00810 -0.0643 0.6453 0.3994
0.500 0.2562 0.01655 0.00808 -0.0643 0.6337 0.4017
0.750 0.2839 0.01654 0.00801 -0.0644 0.6232 0.4043
1.000 0.3109 0.01649 0.00792 -0.0644 0.6116 0.4073
1.250 0.3382 0.01647 0.00782 -0.0646 0.6002 0.4106
1.500 0.3653 0.01640 0.00776 -0.0646 0.5901 0.4133
1.750 0.3921 0.01642 0.00784 -0.0645 0.5795 0.4163
2.000 0.4191 0.01647 0.00793 -0.0645 0.5693 0.4199
2.250 0.4474 0.01654 0.00790 -0.0648 0.5602 0.4242
2.500 0.4739 0.01651 0.00791 -0.0647 0.5495 0.4280
2.750 0.5008 0.01657 0.00804 -0.0647 0.5402 0.4314
3.000 0.5280 0.01664 0.00814 -0.0647 0.5311 0.4355
3.250 0.5555 0.01674 0.00824 -0.0648 0.5223 0.4404
3.500 0.5831 0.01679 0.00830 -0.0650 0.5139 0.4446
3.750 0.6093 0.01689 0.00853 -0.0648 0.5049 0.4488
4.000 0.6375 0.01704 0.00865 -0.0650 0.4974 0.4542
4.250 0.6641 0.01714 0.00883 -0.0650 0.4891 0.4595
4.500 0.6916 0.01728 0.00903 -0.0651 0.4818 0.4641
4.750 0.7179 0.01744 0.00929 -0.0650 0.4737 0.4701
5.000 0.7456 0.01757 0.00942 -0.0651 0.4661 0.4760
5.250 0.7708 0.01771 0.00972 -0.0647 0.4575 0.4815
5.500 0.7984 0.01788 0.00987 -0.0648 0.4498 0.4886
5.750 0.8230 0.01800 0.01016 -0.0644 0.4412 0.4942
6.000 0.8501 0.01817 0.01034 -0.0643 0.4334 0.5009
6.250 0.8743 0.01829 0.01060 -0.0638 0.4246 0.5076
6.500 0.9012 0.01847 0.01081 -0.0637 0.4169 0.5138
6.750 0.9244 0.01860 0.01108 -0.0631 0.4077 0.5215
7.000 0.9495 0.01875 0.01131 -0.0627 0.3995 0.5276
7.250 0.9723 0.01887 0.01158 -0.0619 0.3900 0.5354
7.500 0.9960 0.01904 0.01186 -0.0613 0.3814 0.5425
7.750 1.0189 0.01920 0.01211 -0.0605 0.3721 0.5509
8.000 1.0404 0.01936 0.01243 -0.0595 0.3623 0.5586
8.250 1.0624 0.01956 0.01268 -0.0586 0.3524 0.5675
8.500 1.0816 0.01970 0.01300 -0.0573 0.3414 0.5755
8.750 1.1003 0.01990 0.01333 -0.0558 0.3294 0.5850
9.000 1.1173 0.02010 0.01367 -0.0541 0.3168 0.5932
9.250 1.1329 0.02037 0.01400 -0.0523 0.3026 0.6033
9.500 1.1451 0.02064 0.01441 -0.0498 0.2869 0.6121
9.750 1.1536 0.02097 0.01483 -0.0468 0.2689 0.6219
10.000 1.1600 0.02153 0.01543 -0.0437 0.2479 0.6320
10.250 1.1648 0.02228 0.01620 -0.0406 0.2218 0.6416
10.500 1.1654 0.02339 0.01723 -0.0373 0.1956 0.6524
10.750 1.1623 0.02479 0.01856 -0.0339 0.1744 0.6621
11.000 1.1610 0.02628 0.02004 -0.0311 0.1557 0.6725
11.250 1.1592 0.02794 0.02170 -0.0286 0.1407 0.6842
11.500 1.1570 0.02975 0.02354 -0.0264 0.1286 0.6960
12.000 1.1530 0.03376 0.02770 -0.0230 0.1090 0.7218
12.250 1.1512 0.03597 0.03000 -0.0218 0.1011 0.7366
12.500 1.1475 0.03844 0.03254 -0.0208 0.0943 0.7529
12.750 1.1469 0.04079 0.03505 -0.0200 0.0878 0.7717
13.000 1.1436 0.04343 0.03781 -0.0194 0.0823 0.7939
13.250 1.1400 0.04602 0.04056 -0.0186 0.0770 0.8226
13.500 1.1346 0.04823 0.04301 -0.0171 0.0727 0.8787
13.750 1.1255 0.05112 0.04591 -0.0165 0.0687 1.0000
14.000 1.1283 0.05406 0.04896 -0.0173 0.0641 1.0000
14.250 1.1275 0.05736 0.05228 -0.0183 0.0600 1.0000
14.500 1.1260 0.06066 0.05556 -0.0188 0.0561 1.0000
14.750 1.1266 0.06397 0.05897 -0.0199 0.0524 1.0000
15.000 1.1257 0.06744 0.06244 -0.0210 0.0494 1.0000
15.250 1.1263 0.07064 0.06566 -0.0215 0.0463 1.0000
15.500 1.1261 0.07427 0.06940 -0.0229 0.0434 1.0000
15.750 1.1260 0.07785 0.07302 -0.0242 0.0411 1.0000
16.000 1.1282 0.08088 0.07599 -0.0248 0.0385 1.0000
16.250 1.1269 0.08488 0.08018 -0.0264 0.0366 1.0000
16.500 1.1265 0.08874 0.08414 -0.0280 0.0346 1.0000
16.750 1.1269 0.09241 0.08782 -0.0296 0.0329 1.0000
17.000 1.1299 0.09551 0.09092 -0.0303 0.0310 1.0000
17.250 1.1269 0.10000 0.09561 -0.0324 0.0298 1.0000
17.500 1.1241 0.10450 0.10023 -0.0346 0.0283 1.0000
17.750 1.1237 0.10854 0.10431 -0.0367 0.0270 1.0000
18.000 1.1280 0.11143 0.10713 -0.0377 0.0254 1.0000
18.250 1.1225 0.11653 0.11243 -0.0402 0.0246 1.0000
18.500 1.1158 0.12197 0.11807 -0.0433 0.0238 1.0000
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