NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-015A AIRFOIL (n63015a-il) Reynolds number: 100,000 Max Cl/Cd: 39.26 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63015a-il-100000-n5.txt Download as CSV file: xf-n63015a-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-015A 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7891 0.12005 0.11448 -0.0105 1.0000 0.0326
-15.250 -0.8278 0.10689 0.10116 -0.0188 1.0000 0.0322
-15.000 -0.8603 0.09665 0.09073 -0.0252 1.0000 0.0319
-14.750 -0.8885 0.08835 0.08220 -0.0300 1.0000 0.0318
-14.500 -0.9128 0.08139 0.07501 -0.0335 1.0000 0.0317
-14.250 -0.9338 0.07539 0.06877 -0.0361 1.0000 0.0317
-14.000 -0.9515 0.07015 0.06328 -0.0378 1.0000 0.0318
-13.750 -0.9660 0.06555 0.05841 -0.0389 1.0000 0.0319
-13.500 -0.9772 0.06146 0.05405 -0.0393 1.0000 0.0321
-13.250 -0.9850 0.05782 0.05013 -0.0393 1.0000 0.0323
-13.000 -0.9894 0.05457 0.04659 -0.0390 1.0000 0.0326
-12.750 -0.9893 0.05171 0.04348 -0.0383 1.0000 0.0329
-12.500 -0.9816 0.04940 0.04109 -0.0377 1.0000 0.0334
-12.250 -0.9735 0.04732 0.03892 -0.0371 1.0000 0.0340
-12.000 -0.9648 0.04536 0.03684 -0.0363 1.0000 0.0347
-11.750 -0.9549 0.04350 0.03485 -0.0355 1.0000 0.0355
-11.500 -0.9444 0.04175 0.03297 -0.0346 1.0000 0.0365
-11.250 -0.9327 0.04009 0.03113 -0.0337 1.0000 0.0379
-11.000 -0.9196 0.03851 0.02934 -0.0327 1.0000 0.0394
-10.500 -0.8942 0.03559 0.02641 -0.0307 1.0000 0.0423
-10.250 -0.8812 0.03425 0.02501 -0.0295 1.0000 0.0440
-10.000 -0.8680 0.03294 0.02361 -0.0283 1.0000 0.0460
-9.750 -0.8560 0.03167 0.02226 -0.0268 1.0000 0.0482
-9.500 -0.8466 0.03046 0.02108 -0.0252 1.0000 0.0508
-9.250 -0.8360 0.02939 0.01995 -0.0234 1.0000 0.0542
-9.000 -0.8268 0.02832 0.01883 -0.0213 1.0000 0.0577
-8.750 -0.8190 0.02732 0.01786 -0.0189 1.0000 0.0617
-8.500 -0.8085 0.02643 0.01691 -0.0167 1.0000 0.0673
-8.250 -0.8003 0.02544 0.01598 -0.0142 1.0000 0.0733
-8.000 -0.7911 0.02456 0.01511 -0.0117 1.0000 0.0814
-7.750 -0.7820 0.02375 0.01432 -0.0091 1.0000 0.0916
-7.500 -0.7747 0.02294 0.01357 -0.0061 1.0000 0.1039
-7.250 -0.7686 0.02215 0.01290 -0.0030 1.0000 0.1194
-7.000 -0.7635 0.02138 0.01227 0.0003 1.0000 0.1389
-6.750 -0.7592 0.02065 0.01169 0.0038 1.0000 0.1646
-6.500 -0.7402 0.01958 0.01091 0.0040 0.9938 0.2142
-6.250 -0.7137 0.01830 0.01014 0.0027 0.9830 0.2985
-6.000 -0.6854 0.01746 0.00977 0.0016 0.9729 0.3896
-5.750 -0.6546 0.01710 0.00958 0.0006 0.9626 0.4498
-5.500 -0.6230 0.01692 0.00940 -0.0003 0.9525 0.4891
-5.250 -0.5891 0.01680 0.00924 -0.0016 0.9439 0.5187
-5.000 -0.5587 0.01674 0.00915 -0.0020 0.9330 0.5410
-4.750 -0.5277 0.01670 0.00905 -0.0026 0.9232 0.5621
-4.500 -0.4965 0.01667 0.00892 -0.0031 0.9138 0.5827
-4.250 -0.4686 0.01667 0.00887 -0.0029 0.9029 0.6003
-4.000 -0.4380 0.01666 0.00879 -0.0032 0.8941 0.6154
-3.750 -0.4095 0.01666 0.00875 -0.0031 0.8836 0.6274
-3.500 -0.3810 0.01662 0.00864 -0.0030 0.8741 0.6382
-3.250 -0.3531 0.01652 0.00843 -0.0029 0.8647 0.6492
-3.000 -0.3250 0.01649 0.00836 -0.0028 0.8547 0.6571
-2.750 -0.2967 0.01637 0.00813 -0.0028 0.8466 0.6662
-2.500 -0.2697 0.01633 0.00806 -0.0025 0.8362 0.6735
-2.250 -0.2424 0.01623 0.00785 -0.0024 0.8280 0.6822
-2.000 -0.2150 0.01620 0.00780 -0.0021 0.8184 0.6891
-1.750 -0.1884 0.01611 0.00763 -0.0019 0.8101 0.6980
-1.500 -0.1608 0.01609 0.00760 -0.0017 0.8011 0.7046
-1.250 -0.1347 0.01602 0.00745 -0.0014 0.7929 0.7137
-1.000 -0.1070 0.01601 0.00745 -0.0011 0.7842 0.7200
-0.750 -0.0807 0.01597 0.00735 -0.0008 0.7763 0.7289
-0.500 -0.0535 0.01597 0.00736 -0.0006 0.7678 0.7357
-0.250 -0.0269 0.01594 0.00731 -0.0003 0.7601 0.7443
0.000 0.0000 0.01595 0.00733 0.0000 0.7516 0.7516
0.250 0.0269 0.01594 0.00731 0.0003 0.7443 0.7601
0.500 0.0535 0.01597 0.00736 0.0006 0.7357 0.7678
0.750 0.0807 0.01597 0.00735 0.0008 0.7289 0.7763
1.000 0.1071 0.01601 0.00745 0.0011 0.7200 0.7842
1.250 0.1347 0.01602 0.00745 0.0014 0.7137 0.7929
1.500 0.1609 0.01609 0.00760 0.0017 0.7046 0.8011
1.750 0.1885 0.01611 0.00763 0.0019 0.6980 0.8101
2.000 0.2150 0.01620 0.00780 0.0021 0.6891 0.8184
2.250 0.2424 0.01623 0.00785 0.0024 0.6822 0.8280
2.500 0.2697 0.01633 0.00806 0.0025 0.6735 0.8362
2.750 0.2967 0.01637 0.00813 0.0028 0.6662 0.8466
3.000 0.3250 0.01649 0.00836 0.0028 0.6571 0.8547
3.250 0.3531 0.01652 0.00843 0.0029 0.6492 0.8647
3.500 0.3810 0.01662 0.00864 0.0030 0.6382 0.8741
3.750 0.4095 0.01666 0.00875 0.0031 0.6273 0.8836
4.000 0.4380 0.01666 0.00879 0.0032 0.6154 0.8941
4.250 0.4686 0.01667 0.00887 0.0029 0.6002 0.9029
4.500 0.4966 0.01667 0.00892 0.0031 0.5827 0.9138
4.750 0.5277 0.01670 0.00905 0.0026 0.5621 0.9232
5.000 0.5587 0.01674 0.00914 0.0020 0.5410 0.9331
5.250 0.5891 0.01680 0.00924 0.0016 0.5187 0.9440
5.500 0.6231 0.01692 0.00940 0.0003 0.4891 0.9525
5.750 0.6546 0.01710 0.00958 -0.0006 0.4498 0.9626
6.000 0.6854 0.01746 0.00976 -0.0016 0.3895 0.9729
6.250 0.7137 0.01830 0.01014 -0.0027 0.2983 0.9831
6.500 0.7403 0.01958 0.01091 -0.0041 0.2141 0.9939
6.750 0.7592 0.02064 0.01168 -0.0038 0.1647 1.0000
7.000 0.7634 0.02137 0.01227 -0.0003 0.1389 1.0000
7.250 0.7686 0.02214 0.01290 0.0030 0.1194 1.0000
7.500 0.7748 0.02294 0.01357 0.0061 0.1039 1.0000
7.750 0.7821 0.02375 0.01432 0.0091 0.0915 1.0000
8.000 0.7912 0.02456 0.01511 0.0117 0.0814 1.0000
8.250 0.8004 0.02544 0.01598 0.0142 0.0733 1.0000
8.500 0.8086 0.02643 0.01691 0.0166 0.0672 1.0000
8.750 0.8192 0.02732 0.01786 0.0188 0.0617 1.0000
9.000 0.8271 0.02832 0.01883 0.0212 0.0576 1.0000
9.250 0.8363 0.02939 0.01995 0.0234 0.0541 1.0000
9.500 0.8470 0.03046 0.02108 0.0251 0.0507 1.0000
9.750 0.8564 0.03167 0.02226 0.0268 0.0482 1.0000
10.000 0.8684 0.03294 0.02361 0.0282 0.0460 1.0000
10.250 0.8817 0.03424 0.02500 0.0295 0.0440 1.0000
10.500 0.8947 0.03559 0.02640 0.0306 0.0423 1.0000
10.750 0.9070 0.03697 0.02781 0.0317 0.0408 1.0000
11.000 0.9202 0.03851 0.02934 0.0326 0.0394 1.0000
11.250 0.9333 0.04008 0.03113 0.0336 0.0379 1.0000
11.500 0.9450 0.04175 0.03297 0.0345 0.0365 1.0000
11.750 0.9556 0.04350 0.03485 0.0354 0.0354 1.0000
12.000 0.9655 0.04536 0.03684 0.0362 0.0347 1.0000
12.250 0.9744 0.04732 0.03892 0.0370 0.0340 1.0000
12.500 0.9825 0.04940 0.04109 0.0376 0.0334 1.0000
12.750 0.9902 0.05171 0.04349 0.0382 0.0329 1.0000
13.000 0.9902 0.05459 0.04661 0.0388 0.0326 1.0000
13.250 0.9858 0.05785 0.05016 0.0392 0.0323 1.0000
13.500 0.9781 0.06148 0.05408 0.0392 0.0321 1.0000
13.750 0.9669 0.06557 0.05844 0.0387 0.0319 1.0000
14.000 0.9524 0.07020 0.06333 0.0377 0.0318 1.0000
14.250 0.9347 0.07544 0.06883 0.0359 0.0317 1.0000
14.500 0.9137 0.08145 0.07508 0.0333 0.0317 1.0000
14.750 0.8892 0.08846 0.08232 0.0297 0.0318 1.0000
15.000 0.8611 0.09679 0.09087 0.0249 0.0319 1.0000
15.250 0.8283 0.10713 0.10141 0.0184 0.0322 1.0000
15.500 0.7894 0.12039 0.11482 0.0101 0.0326 1.0000
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