NREL's S819 Airfoil (s819-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S819 Airfoil (s819-nr) Reynolds number: 100,000 Max Cl/Cd: 38.37 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s819-nr-100000.txt Download as CSV file: xf-s819-nr-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6341 0.13185 0.12678 -0.0367 1.0000 0.1551
-15.500 -0.7162 0.11320 0.10822 -0.0449 1.0000 0.1580
-15.250 -0.9843 0.08100 0.07573 -0.0641 1.0000 0.1659
-15.000 -0.9928 0.07576 0.07035 -0.0648 1.0000 0.1638
-14.750 -1.0216 0.07027 0.06465 -0.0662 1.0000 0.1615
-14.500 -1.0578 0.06533 0.05946 -0.0673 1.0000 0.1591
-14.250 -1.1040 0.06118 0.05502 -0.0676 1.0000 0.1569
-14.000 -1.1318 0.05850 0.05209 -0.0666 1.0000 0.1554
-13.750 -1.1654 0.05700 0.05037 -0.0642 1.0000 0.1541
-13.250 -1.0315 0.05388 0.04679 -0.0637 1.0000 0.1438
-13.000 -0.9432 0.05648 0.04899 -0.0618 1.0000 0.1252
-12.750 -0.8113 0.06234 0.05436 -0.0575 1.0000 0.0941
-12.500 -0.7469 0.06474 0.05652 -0.0546 1.0000 0.0807
-12.250 -0.6744 0.06848 0.06016 -0.0504 1.0000 0.0691
-12.000 -0.6741 0.06622 0.05769 -0.0508 1.0000 0.0664
-11.750 -0.5633 0.07571 0.06728 -0.0426 1.0000 0.0557
-11.500 -0.4769 0.08579 0.07756 -0.0352 1.0000 0.0509
-11.250 -0.4361 0.08977 0.08160 -0.0317 1.0000 0.0484
-11.000 -0.4142 0.09061 0.08245 -0.0300 1.0000 0.0472
-10.750 -0.3988 0.09054 0.08242 -0.0287 1.0000 0.0476
-10.500 -0.3876 0.08971 0.08158 -0.0278 1.0000 0.0474
-10.250 -0.3804 0.08829 0.08018 -0.0271 1.0000 0.0481
-10.000 -0.3757 0.08649 0.07837 -0.0265 1.0000 0.0487
-9.750 -0.3715 0.08457 0.07643 -0.0260 1.0000 0.0485
-9.500 -0.3706 0.08227 0.07410 -0.0254 1.0000 0.0489
-9.250 -0.3699 0.07996 0.07176 -0.0249 1.0000 0.0488
-9.000 -0.3698 0.07765 0.06941 -0.0242 1.0000 0.0486
-8.750 -0.3727 0.07504 0.06676 -0.0236 1.0000 0.0489
-8.500 -0.3746 0.07268 0.06435 -0.0228 1.0000 0.0487
-8.250 -0.3797 0.07004 0.06167 -0.0219 1.0000 0.0490
-8.000 -0.3864 0.06738 0.05897 -0.0209 1.0000 0.0492
-7.750 -0.3950 0.06468 0.05623 -0.0197 1.0000 0.0493
-7.500 -0.4066 0.06193 0.05344 -0.0183 1.0000 0.0495
-7.250 -0.4219 0.05913 0.05060 -0.0165 1.0000 0.0497
-7.000 -0.4394 0.05646 0.04790 -0.0144 1.0000 0.0496
-6.750 -0.4624 0.05377 0.04519 -0.0116 1.0000 0.0495
-6.500 -0.4911 0.05122 0.04263 -0.0081 1.0000 0.0493
-6.250 -0.1789 0.08973 0.08281 0.0012 1.0000 0.4368
-6.000 -0.1684 0.09011 0.08321 0.0040 1.0000 0.4536
-5.750 -0.1915 0.09046 0.08367 0.0082 1.0000 0.4563
-5.500 -0.1844 0.08975 0.08300 0.0111 1.0000 0.4619
-5.250 -0.2458 0.09075 0.08414 0.0143 0.9961 0.4583
-5.000 -0.2033 0.09014 0.08345 0.0096 0.9882 0.4740
-4.750 -0.1486 0.08654 0.07974 0.0036 0.9830 0.4746
-4.500 -0.0979 0.08343 0.07657 -0.0019 0.9752 0.4757
-4.250 -0.0499 0.08071 0.07380 -0.0073 0.9676 0.4773
-4.000 -0.0044 0.07823 0.07129 -0.0128 0.9595 0.4796
-3.750 -0.0118 0.07820 0.07122 -0.0167 0.9438 0.4897
-3.500 0.0324 0.07496 0.06798 -0.0208 0.9331 0.4906
-3.250 0.0888 0.07167 0.06467 -0.0270 0.9282 0.4917
-3.000 0.1329 0.06910 0.06212 -0.0311 0.9164 0.4934
-2.750 0.1757 0.06675 0.05977 -0.0353 0.9046 0.4961
-2.500 0.1668 0.06644 0.05941 -0.0371 0.8873 0.5061
-2.250 0.2179 0.06333 0.05630 -0.0414 0.8751 0.5070
-2.000 0.2661 0.06076 0.05371 -0.0454 0.8608 0.5087
-1.750 0.3062 0.05884 0.05174 -0.0483 0.8433 0.5116
-1.500 0.3324 0.05760 0.05045 -0.0497 0.8245 0.5166
-1.250 0.1430 0.04462 0.03697 -0.0495 0.8050 0.4425
-1.000 0.1717 0.04409 0.03644 -0.0491 0.7902 0.4432
-0.750 0.1576 0.03911 0.03124 -0.0515 0.7755 0.4409
-0.500 0.1465 0.03317 0.02487 -0.0554 0.7617 0.4425
-0.250 0.1745 0.03297 0.02469 -0.0550 0.7488 0.4436
0.000 0.2029 0.03257 0.02428 -0.0551 0.7368 0.4450
0.250 0.2267 0.03197 0.02365 -0.0551 0.7239 0.4467
0.500 0.2475 0.03120 0.02284 -0.0551 0.7108 0.4489
0.750 0.2697 0.03018 0.02172 -0.0558 0.6986 0.4517
1.000 0.2956 0.02870 0.01998 -0.0579 0.6878 0.4562
1.250 0.3205 0.02806 0.01928 -0.0584 0.6759 0.4595
1.500 0.3438 0.02814 0.01945 -0.0575 0.6638 0.4618
1.750 0.3701 0.02807 0.01940 -0.0574 0.6533 0.4649
2.000 0.3976 0.02766 0.01892 -0.0580 0.6429 0.4691
2.250 0.4224 0.02702 0.01815 -0.0591 0.6313 0.4743
2.500 0.4487 0.02703 0.01824 -0.0587 0.6217 0.4770
2.750 0.4743 0.02706 0.01835 -0.0585 0.6118 0.4803
3.000 0.4988 0.02701 0.01833 -0.0584 0.6015 0.4848
3.250 0.5308 0.02662 0.01778 -0.0599 0.5933 0.4907
3.500 0.5513 0.02687 0.01824 -0.0588 0.5828 0.4940
3.750 0.5801 0.02696 0.01835 -0.0591 0.5753 0.4990
4.000 0.6049 0.02696 0.01836 -0.0595 0.5654 0.5062
4.250 0.6303 0.02718 0.01873 -0.0589 0.5576 0.5104
4.500 0.6542 0.02742 0.01909 -0.0585 0.5489 0.5162
4.750 0.6824 0.02751 0.01918 -0.0591 0.5415 0.5234
5.000 0.7048 0.02781 0.01969 -0.0583 0.5329 0.5283
5.250 0.7328 0.02798 0.01988 -0.0587 0.5256 0.5359
5.500 0.7557 0.02822 0.02027 -0.0581 0.5168 0.5416
5.750 0.7814 0.02846 0.02063 -0.0578 0.5090 0.5485
6.000 0.8065 0.02863 0.02090 -0.0577 0.5002 0.5564
6.250 0.8295 0.02895 0.02139 -0.0569 0.4920 0.5632
6.500 0.8572 0.02901 0.02151 -0.0570 0.4831 0.5723
6.750 0.8768 0.02938 0.02210 -0.0557 0.4739 0.5792
7.000 0.9098 0.02922 0.02190 -0.0564 0.4651 0.5890
7.250 0.9255 0.02963 0.02259 -0.0546 0.4547 0.5964
7.500 0.9529 0.02963 0.02266 -0.0544 0.4452 0.6061
7.750 0.9786 0.02959 0.02271 -0.0539 0.4347 0.6161
8.000 0.9962 0.02980 0.02314 -0.0522 0.4234 0.6246
8.250 1.0213 0.02976 0.02317 -0.0517 0.4121 0.6361
8.500 1.0494 0.02951 0.02294 -0.0512 0.4007 0.6467
8.750 1.0643 0.02961 0.02329 -0.0491 0.3880 0.6565
9.000 1.0821 0.02965 0.02348 -0.0475 0.3745 0.6683
9.250 1.0984 0.02963 0.02362 -0.0454 0.3607 0.6795
9.500 1.1131 0.02957 0.02369 -0.0431 0.3458 0.6906
9.750 1.1260 0.02956 0.02378 -0.0407 0.3297 0.7027
10.000 1.1357 0.02960 0.02392 -0.0379 0.3124 0.7158
10.250 1.1408 0.02973 0.02414 -0.0344 0.2946 0.7285
10.500 1.1399 0.02998 0.02443 -0.0300 0.2770 0.7407
10.750 1.1338 0.03069 0.02527 -0.0256 0.2577 0.7536
11.000 1.1287 0.03162 0.02625 -0.0217 0.2378 0.7680
11.250 1.1234 0.03279 0.02737 -0.0182 0.2193 0.7837
11.500 1.1173 0.03427 0.02879 -0.0151 0.2022 0.8010
11.750 1.1113 0.03597 0.03048 -0.0123 0.1865 0.8208
12.000 1.1059 0.03767 0.03217 -0.0095 0.1729 0.8443
12.250 1.0992 0.03922 0.03377 -0.0065 0.1615 0.8777
12.500 1.0903 0.04067 0.03542 -0.0038 0.1514 1.0000
12.750 1.0994 0.04336 0.03800 -0.0054 0.1383 1.0000
13.000 1.1063 0.04597 0.04051 -0.0062 0.1272 1.0000
13.250 1.1150 0.04837 0.04277 -0.0066 0.1170 1.0000
13.500 1.1166 0.05111 0.04557 -0.0069 0.1089 1.0000
13.750 1.1219 0.05382 0.04828 -0.0070 0.1011 1.0000
14.000 1.1374 0.05580 0.04999 -0.0070 0.0923 1.0000
14.250 1.1295 0.05944 0.05395 -0.0074 0.0881 1.0000
14.500 1.1370 0.06187 0.05630 -0.0076 0.0819 1.0000
14.750 1.1378 0.06527 0.05985 -0.0080 0.0773 1.0000
15.000 1.1333 0.06898 0.06375 -0.0087 0.0736 1.0000
15.250 1.1510 0.07110 0.06566 -0.0085 0.0679 1.0000
15.500 1.1361 0.07587 0.07077 -0.0099 0.0661 1.0000
15.750 1.1247 0.08063 0.07578 -0.0114 0.0640 1.0000
16.000 1.1147 0.08540 0.08074 -0.0132 0.0619 1.0000
16.250 1.1345 0.08731 0.08242 -0.0127 0.0574 1.0000
16.500 1.1135 0.09346 0.08888 -0.0156 0.0569 1.0000
16.750 1.0897 0.10040 0.09611 -0.0192 0.0564 1.0000
17.000 1.0644 0.10809 0.10408 -0.0235 0.0562 1.0000
17.250 1.0373 0.11665 0.11289 -0.0286 0.0563 1.0000
17.500 1.0075 0.12630 0.12275 -0.0345 0.0567 1.0000
17.750 0.9755 0.13713 0.13377 -0.0414 0.0573 1.0000
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