NREL's S819 Airfoil (s819-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S819 Airfoil (s819-nr) Reynolds number: 200,000 Max Cl/Cd: 54.82 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s819-nr-200000-n5.txt Download as CSV file: xf-s819-nr-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8231 0.09156 0.08574 -0.0581 1.0000 0.0212
-15.250 -0.8421 0.08836 0.08235 -0.0592 1.0000 0.0214
-15.000 -0.8549 0.08535 0.07919 -0.0599 1.0000 0.0215
-14.750 -0.8786 0.08262 0.07626 -0.0605 1.0000 0.0217
-14.500 -0.9022 0.08013 0.07358 -0.0608 1.0000 0.0218
-14.250 -0.9203 0.07783 0.07112 -0.0606 1.0000 0.0218
-14.000 -0.9428 0.07600 0.06912 -0.0599 1.0000 0.0219
-13.750 -0.9538 0.07412 0.06709 -0.0589 1.0000 0.0219
-13.500 -0.9653 0.07240 0.06525 -0.0576 1.0000 0.0220
-11.500 -0.6252 0.06285 0.05543 -0.0461 1.0000 0.0134
-11.250 -0.5717 0.06633 0.05915 -0.0416 1.0000 0.0123
-11.000 -0.5476 0.06704 0.05990 -0.0392 1.0000 0.0119
-10.750 -0.5249 0.06774 0.06062 -0.0369 1.0000 0.0115
-10.500 -0.5055 0.06810 0.06101 -0.0349 1.0000 0.0112
-10.250 -0.4880 0.06829 0.06122 -0.0330 1.0000 0.0109
-10.000 -0.4717 0.06841 0.06138 -0.0311 1.0000 0.0108
-9.750 -0.4579 0.06816 0.06114 -0.0295 1.0000 0.0106
-9.500 -0.4444 0.06805 0.06108 -0.0278 1.0000 0.0106
-9.250 -0.4335 0.06758 0.06065 -0.0263 1.0000 0.0106
-9.000 -0.4250 0.06675 0.05984 -0.0249 1.0000 0.0105
-8.750 -0.4193 0.06576 0.05891 -0.0234 1.0000 0.0108
-8.500 -0.4129 0.06483 0.05802 -0.0220 1.0000 0.0106
-8.250 -0.4067 0.06421 0.05747 -0.0203 1.0000 0.0108
-8.000 -0.4054 0.06296 0.05626 -0.0187 1.0000 0.0109
-7.750 -0.4100 0.06100 0.05431 -0.0173 0.9999 0.0109
-7.500 -0.3984 0.05722 0.05048 -0.0215 0.9953 0.0111
-7.250 -0.3948 0.05277 0.04593 -0.0256 0.9893 0.0113
-7.000 -0.3930 0.04784 0.04088 -0.0303 0.9830 0.0111
-6.750 -0.3987 0.04246 0.03536 -0.0346 0.9733 0.0114
-6.500 -0.4048 0.03729 0.03003 -0.0385 0.9608 0.0117
-6.000 -0.4186 0.02872 0.02112 -0.0432 0.9233 0.0118
-5.750 -0.4103 0.02627 0.01851 -0.0449 0.9041 0.0131
-5.500 -0.4004 0.02281 0.01474 -0.0493 0.8846 0.0142
-5.250 -0.3739 0.02132 0.01303 -0.0519 0.8696 0.0148
-5.000 -0.3432 0.02024 0.01174 -0.0542 0.8542 0.0154
-4.750 -0.3118 0.01943 0.01072 -0.0562 0.8378 0.0162
-4.500 -0.2817 0.01884 0.00994 -0.0575 0.8207 0.0171
-4.250 -0.2542 0.01830 0.00921 -0.0583 0.8032 0.0190
-4.000 -0.2280 0.01789 0.00867 -0.0587 0.7859 0.0243
-3.750 -0.2226 0.01508 0.00658 -0.0588 0.7685 0.2803
-3.500 -0.1957 0.01497 0.00653 -0.0592 0.7526 0.3127
-3.250 -0.1676 0.01525 0.00673 -0.0596 0.7373 0.3323
-2.750 -0.1132 0.01532 0.00666 -0.0598 0.7079 0.3415
-2.500 -0.0862 0.01524 0.00648 -0.0598 0.6938 0.3429
-2.250 -0.0593 0.01515 0.00631 -0.0598 0.6802 0.3443
-2.000 -0.0323 0.01507 0.00614 -0.0599 0.6672 0.3459
-1.750 -0.0053 0.01501 0.00598 -0.0599 0.6548 0.3474
-1.500 0.0217 0.01495 0.00583 -0.0600 0.6426 0.3490
-1.250 0.0486 0.01488 0.00572 -0.0600 0.6305 0.3505
-1.000 0.0755 0.01482 0.00565 -0.0600 0.6191 0.3520
-0.750 0.1024 0.01480 0.00560 -0.0600 0.6082 0.3536
-0.500 0.1294 0.01476 0.00555 -0.0601 0.5970 0.3555
-0.250 0.1566 0.01474 0.00551 -0.0601 0.5866 0.3575
0.000 0.1836 0.01475 0.00546 -0.0601 0.5765 0.3597
0.250 0.2108 0.01473 0.00542 -0.0602 0.5656 0.3621
0.500 0.2380 0.01474 0.00539 -0.0603 0.5557 0.3646
0.750 0.2649 0.01473 0.00540 -0.0603 0.5462 0.3668
1.000 0.2921 0.01474 0.00545 -0.0604 0.5367 0.3693
1.250 0.3190 0.01478 0.00548 -0.0604 0.5276 0.3721
1.500 0.3462 0.01480 0.00552 -0.0604 0.5178 0.3751
1.750 0.3733 0.01485 0.00554 -0.0605 0.5090 0.3783
2.000 0.4003 0.01489 0.00559 -0.0605 0.5002 0.3810
2.250 0.4273 0.01493 0.00569 -0.0605 0.4921 0.3838
2.500 0.4542 0.01499 0.00579 -0.0605 0.4837 0.3870
2.750 0.4813 0.01506 0.00589 -0.0606 0.4754 0.3905
3.000 0.5081 0.01514 0.00597 -0.0606 0.4672 0.3943
3.250 0.5351 0.01522 0.00610 -0.0606 0.4598 0.3976
3.500 0.5619 0.01530 0.00626 -0.0606 0.4524 0.4011
3.750 0.5887 0.01541 0.00641 -0.0606 0.4454 0.4051
4.000 0.6155 0.01552 0.00656 -0.0605 0.4377 0.4095
4.250 0.6420 0.01565 0.00674 -0.0605 0.4311 0.4134
4.500 0.6688 0.01576 0.00695 -0.0605 0.4243 0.4177
4.750 0.6951 0.01592 0.00715 -0.0604 0.4179 0.4227
5.000 0.7217 0.01605 0.00736 -0.0603 0.4109 0.4277
5.250 0.7474 0.01621 0.00759 -0.0601 0.4034 0.4324
5.500 0.7731 0.01636 0.00783 -0.0599 0.3952 0.4378
5.750 0.7981 0.01654 0.00804 -0.0595 0.3870 0.4430
6.000 0.8233 0.01669 0.00832 -0.0592 0.3783 0.4478
6.250 0.8475 0.01689 0.00855 -0.0588 0.3700 0.4533
6.500 0.8723 0.01706 0.00884 -0.0584 0.3611 0.4588
6.750 0.8959 0.01728 0.00912 -0.0578 0.3528 0.4641
7.000 0.9196 0.01747 0.00942 -0.0573 0.3430 0.4700
7.250 0.9426 0.01770 0.00973 -0.0566 0.3337 0.4760
7.500 0.9645 0.01795 0.01007 -0.0558 0.3238 0.4822
7.750 0.9872 0.01819 0.01041 -0.0551 0.3138 0.4893
8.000 1.0082 0.01846 0.01079 -0.0542 0.3035 0.4956
8.250 1.0277 0.01879 0.01118 -0.0530 0.2919 0.5028
8.500 1.0471 0.01910 0.01159 -0.0518 0.2787 0.5095
8.750 1.0639 0.01945 0.01204 -0.0502 0.2642 0.5169
9.000 1.0777 0.01987 0.01249 -0.0481 0.2472 0.5239
9.250 1.0907 0.02039 0.01306 -0.0461 0.2267 0.5314
9.750 1.1072 0.02205 0.01464 -0.0411 0.1807 0.5468
10.000 1.1128 0.02310 0.01564 -0.0385 0.1615 0.5549
10.250 1.1185 0.02419 0.01676 -0.0362 0.1451 0.5629
10.500 1.1240 0.02536 0.01794 -0.0340 0.1308 0.5715
10.750 1.1282 0.02665 0.01927 -0.0319 0.1182 0.5797
11.000 1.1327 0.02801 0.02066 -0.0300 0.1071 0.5882
11.250 1.1372 0.02945 0.02218 -0.0284 0.0976 0.5970
11.500 1.1401 0.03108 0.02389 -0.0269 0.0896 0.6059
11.750 1.1429 0.03285 0.02574 -0.0257 0.0823 0.6155
12.000 1.1459 0.03471 0.02770 -0.0247 0.0762 0.6250
12.500 1.1489 0.03900 0.03220 -0.0234 0.0657 0.6455
12.750 1.1505 0.04130 0.03464 -0.0230 0.0613 0.6563
13.250 1.1507 0.04654 0.04012 -0.0229 0.0535 0.6805
13.500 1.1497 0.04941 0.04313 -0.0231 0.0502 0.6932
13.750 1.1461 0.05268 0.04650 -0.0235 0.0472 0.7064
14.000 1.1470 0.05554 0.04954 -0.0239 0.0444 0.7219
14.250 1.1449 0.05882 0.05297 -0.0245 0.0416 0.7387
14.500 1.1396 0.06256 0.05681 -0.0254 0.0393 0.7569
14.750 1.1378 0.06588 0.06032 -0.0260 0.0371 0.7803
15.000 1.1351 0.06927 0.06391 -0.0266 0.0350 0.8113
15.250 1.1274 0.07270 0.06757 -0.0266 0.0333 0.8747
15.500 1.1179 0.07664 0.07162 -0.0274 0.0319 1.0000
15.750 1.1162 0.08058 0.07566 -0.0290 0.0302 1.0000
16.000 1.1146 0.08460 0.07978 -0.0306 0.0284 1.0000
16.250 1.1110 0.08900 0.08425 -0.0325 0.0268 1.0000
16.500 1.1052 0.09377 0.08908 -0.0347 0.0256 1.0000
16.750 1.1024 0.09818 0.09359 -0.0366 0.0243 1.0000
17.000 1.1002 0.10256 0.09808 -0.0387 0.0230 1.0000
17.250 1.0970 0.10716 0.10277 -0.0409 0.0219 1.0000
17.500 1.0923 0.11206 0.10775 -0.0433 0.0210 1.0000
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