NACA 63-415 AIRFOIL (n63415-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-415 AIRFOIL (n63415-il) Reynolds number: 50,000 Max Cl/Cd: 27.76 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63415-il-50000-n5.txt Download as CSV file: xf-n63415-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-415 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4864 0.10374 0.09610 -0.0490 1.0000 0.0653
-12.000 -0.5035 0.09531 0.08770 -0.0538 1.0000 0.0650
-11.750 -0.5277 0.08661 0.07900 -0.0592 1.0000 0.0645
-11.500 -0.5563 0.07865 0.07102 -0.0643 1.0000 0.0640
-11.250 -0.5852 0.07205 0.06435 -0.0682 1.0000 0.0635
-11.000 -0.6120 0.06686 0.05905 -0.0703 1.0000 0.0632
-10.750 -0.6369 0.06283 0.05491 -0.0707 1.0000 0.0633
-10.500 -0.6597 0.05982 0.05179 -0.0692 1.0000 0.0633
-10.250 -0.6788 0.05715 0.04899 -0.0670 1.0000 0.0636
-10.000 -0.6949 0.05466 0.04631 -0.0643 1.0000 0.0643
-9.750 -0.7084 0.05238 0.04380 -0.0613 1.0000 0.0651
-9.500 -0.7198 0.05026 0.04139 -0.0580 1.0000 0.0659
-9.250 -0.7245 0.04831 0.03926 -0.0550 1.0000 0.0669
-9.000 -0.7218 0.04670 0.03763 -0.0525 1.0000 0.0683
-8.750 -0.7190 0.04511 0.03591 -0.0500 1.0000 0.0695
-8.500 -0.7149 0.04357 0.03421 -0.0476 1.0000 0.0713
-8.250 -0.7092 0.04207 0.03251 -0.0454 1.0000 0.0736
-8.000 -0.6785 0.03985 0.02974 -0.0475 0.9923 0.0775
-7.750 -0.6463 0.03810 0.02806 -0.0491 0.9857 0.0812
-7.500 -0.6146 0.03667 0.02643 -0.0506 0.9784 0.0866
-7.250 -0.5801 0.03526 0.02488 -0.0521 0.9723 0.0920
-7.000 -0.5506 0.03415 0.02375 -0.0529 0.9644 0.0982
-6.750 -0.5167 0.03301 0.02250 -0.0546 0.9583 0.1067
-6.500 -0.4906 0.03199 0.02141 -0.0550 0.9493 0.1159
-6.250 -0.4596 0.03080 0.02024 -0.0567 0.9428 0.1302
-6.000 -0.4374 0.02964 0.01914 -0.0570 0.9332 0.1484
-5.750 -0.4092 0.02802 0.01783 -0.0591 0.9265 0.1846
-5.500 -0.3918 0.02646 0.01684 -0.0594 0.9167 0.2542
-5.250 -0.3628 0.02563 0.01686 -0.0603 0.9108 0.3914
-5.000 -0.3421 0.02586 0.01720 -0.0588 0.9009 0.4641
-4.750 -0.3090 0.02630 0.01753 -0.0592 0.8950 0.5207
-4.500 -0.2884 0.02689 0.01804 -0.0571 0.8854 0.5556
-4.250 -0.2581 0.02761 0.01868 -0.0560 0.8793 0.5859
-4.000 -0.2372 0.02810 0.01906 -0.0540 0.8704 0.6077
-3.750 -0.2091 0.02855 0.01937 -0.0529 0.8639 0.6267
-3.500 -0.1855 0.02881 0.01950 -0.0516 0.8561 0.6432
-3.250 -0.1604 0.02888 0.01941 -0.0509 0.8485 0.6581
-3.000 -0.1274 0.02894 0.01931 -0.0512 0.8437 0.6692
-2.750 -0.1109 0.02899 0.01927 -0.0494 0.8337 0.6796
-2.500 -0.0794 0.02880 0.01890 -0.0504 0.8281 0.6920
-2.250 -0.0605 0.02894 0.01897 -0.0486 0.8196 0.6999
-2.000 -0.0327 0.02880 0.01869 -0.0490 0.8131 0.7108
-1.750 -0.0065 0.02880 0.01860 -0.0486 0.8067 0.7192
-1.500 0.0143 0.02880 0.01851 -0.0479 0.7984 0.7289
-1.250 0.0453 0.02870 0.01830 -0.0483 0.7935 0.7376
-1.000 0.0622 0.02881 0.01836 -0.0470 0.7845 0.7466
-0.750 0.0898 0.02876 0.01823 -0.0471 0.7786 0.7554
-0.500 0.1140 0.02879 0.01820 -0.0467 0.7722 0.7641
-0.250 0.1345 0.02890 0.01827 -0.0459 0.7642 0.7734
0.000 0.1648 0.02881 0.01813 -0.0462 0.7595 0.7817
0.250 0.1803 0.02909 0.01839 -0.0450 0.7506 0.7919
0.500 0.2063 0.02910 0.01839 -0.0446 0.7449 0.8002
0.750 0.2314 0.02918 0.01844 -0.0445 0.7389 0.8108
1.000 0.2480 0.02945 0.01873 -0.0430 0.7307 0.8201
1.250 0.2778 0.02940 0.01866 -0.0433 0.7262 0.8301
1.500 0.2917 0.02981 0.01910 -0.0417 0.7173 0.8416
1.750 0.3163 0.02988 0.01920 -0.0412 0.7116 0.8519
2.000 0.3453 0.02987 0.01919 -0.0413 0.7071 0.8629
2.250 0.3561 0.03041 0.01980 -0.0395 0.6975 0.8764
2.500 0.3862 0.03036 0.01979 -0.0397 0.6930 0.8884
2.750 0.4003 0.03090 0.02040 -0.0385 0.6841 0.9033
3.000 0.4297 0.03099 0.02056 -0.0389 0.6783 0.9177
3.250 0.4695 0.03084 0.02048 -0.0407 0.6747 0.9312
3.500 0.4887 0.03169 0.02144 -0.0413 0.6640 0.9508
3.750 0.5357 0.03161 0.02147 -0.0446 0.6596 0.9657
4.000 0.5609 0.03241 0.02238 -0.0464 0.6495 1.0000
4.250 0.5901 0.03249 0.02250 -0.0470 0.6439 1.0000
4.500 0.6030 0.03341 0.02348 -0.0465 0.6341 1.0000
4.750 0.6345 0.03357 0.02369 -0.0474 0.6279 1.0000
5.000 0.6521 0.03445 0.02463 -0.0473 0.6184 1.0000
5.250 0.6836 0.03461 0.02489 -0.0481 0.6117 1.0000
5.500 0.7014 0.03549 0.02586 -0.0478 0.6016 1.0000
5.750 0.7352 0.03544 0.02590 -0.0485 0.5948 1.0000
6.000 0.7506 0.03637 0.02693 -0.0478 0.5833 1.0000
6.250 0.7921 0.03570 0.02641 -0.0486 0.5771 1.0000
6.500 0.8056 0.03658 0.02740 -0.0475 0.5640 1.0000
6.750 0.8273 0.03687 0.02781 -0.0467 0.5522 1.0000
7.000 0.8740 0.03550 0.02662 -0.0474 0.5438 1.0000
7.250 0.8909 0.03587 0.02713 -0.0460 0.5293 1.0000
7.500 0.9106 0.03592 0.02733 -0.0447 0.5144 1.0000
7.750 0.9336 0.03559 0.02714 -0.0433 0.4983 1.0000
8.000 0.9595 0.03489 0.02657 -0.0419 0.4801 1.0000
8.250 0.9707 0.03514 0.02692 -0.0397 0.4587 1.0000
8.500 0.9821 0.03538 0.02726 -0.0375 0.4339 1.0000
8.750 0.9907 0.03593 0.02787 -0.0354 0.4049 1.0000
9.000 1.0014 0.03636 0.02826 -0.0335 0.3697 1.0000
9.250 1.0092 0.03722 0.02897 -0.0315 0.3283 1.0000
9.500 1.0144 0.03848 0.02993 -0.0296 0.2840 1.0000
9.750 1.0139 0.04052 0.03167 -0.0280 0.2440 1.0000
10.000 1.0108 0.04305 0.03392 -0.0267 0.2110 1.0000
10.250 1.0077 0.04581 0.03647 -0.0258 0.1835 1.0000
10.500 1.0058 0.04862 0.03911 -0.0250 0.1619 1.0000
10.750 1.0053 0.05143 0.04180 -0.0244 0.1441 1.0000
11.000 1.0066 0.05416 0.04444 -0.0239 0.1300 1.0000
11.250 1.0100 0.05674 0.04694 -0.0234 0.1189 1.0000
11.500 1.0147 0.05922 0.04938 -0.0230 0.1095 1.0000
11.750 1.0233 0.06144 0.05167 -0.0225 0.1009 1.0000
12.000 1.0328 0.06353 0.05368 -0.0220 0.0948 1.0000
12.250 1.0448 0.06559 0.05592 -0.0215 0.0883 1.0000
12.500 1.0578 0.06741 0.05765 -0.0209 0.0832 1.0000
12.750 1.0724 0.06951 0.06005 -0.0204 0.0785 1.0000
13.000 1.0853 0.07160 0.06224 -0.0201 0.0743 1.0000
13.250 1.1014 0.07352 0.06418 -0.0196 0.0707 1.0000
13.500 1.1081 0.07666 0.06766 -0.0196 0.0678 1.0000
13.750 1.1137 0.07981 0.07102 -0.0199 0.0652 1.0000
14.000 1.1205 0.08268 0.07398 -0.0201 0.0629 1.0000
14.250 1.1273 0.08580 0.07720 -0.0204 0.0610 1.0000
14.500 1.1165 0.09107 0.08284 -0.0219 0.0600 1.0000
14.750 1.1032 0.09690 0.08900 -0.0240 0.0592 1.0000
15.000 1.0863 0.10354 0.09593 -0.0269 0.0586 1.0000
15.250 1.0648 0.11131 0.10398 -0.0309 0.0584 1.0000
15.500 1.0373 0.12088 0.11380 -0.0364 0.0585 1.0000
15.750 1.0025 0.13317 0.12632 -0.0441 0.0591 1.0000
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