NACA 4415 (naca4415-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4415 (naca4415-il) Reynolds number: 50,000 Max Cl/Cd: 27.4 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4415-il-50000-n5.txt Download as CSV file: xf-naca4415-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4415
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3774 0.10454 0.09726 -0.0481 1.0000 0.0748
-10.000 -0.3910 0.10060 0.09341 -0.0482 1.0000 0.0756
-9.750 -0.4080 0.09637 0.08929 -0.0483 1.0000 0.0762
-9.500 -0.4318 0.09148 0.08452 -0.0487 1.0000 0.0770
-9.250 -0.4600 0.08627 0.07943 -0.0491 1.0000 0.0770
-9.000 -0.4999 0.07993 0.07320 -0.0502 1.0000 0.0765
-8.750 -0.5522 0.07381 0.06716 -0.0497 1.0000 0.0752
-8.500 -0.5978 0.06782 0.06109 -0.0486 1.0000 0.0746
-8.250 -0.6266 0.06227 0.05531 -0.0479 0.9987 0.0751
-8.000 -0.6329 0.05470 0.04708 -0.0518 0.9890 0.0779
-7.750 -0.6183 0.05101 0.04302 -0.0538 0.9816 0.0811
-7.500 -0.5984 0.04882 0.04060 -0.0549 0.9739 0.0854
-7.250 -0.5833 0.04536 0.03659 -0.0557 0.9661 0.0902
-7.000 -0.5564 0.04412 0.03522 -0.0569 0.9593 0.0957
-6.750 -0.5372 0.04194 0.03265 -0.0570 0.9513 0.1017
-6.500 -0.5089 0.04063 0.03111 -0.0582 0.9447 0.1092
-6.250 -0.4870 0.03948 0.02982 -0.0580 0.9364 0.1159
-6.000 -0.4581 0.03802 0.02797 -0.0591 0.9298 0.1257
-5.750 -0.4351 0.03745 0.02740 -0.0587 0.9212 0.1336
-5.500 -0.4048 0.03653 0.02630 -0.0597 0.9145 0.1438
-5.250 -0.3818 0.03567 0.02514 -0.0593 0.9058 0.1546
-5.000 -0.3515 0.03510 0.02456 -0.0601 0.8987 0.1653
-4.750 -0.3264 0.03449 0.02385 -0.0599 0.8904 0.1754
-4.500 -0.2972 0.03381 0.02294 -0.0604 0.8828 0.1876
-4.250 -0.2689 0.03331 0.02239 -0.0606 0.8753 0.1986
-4.000 -0.2419 0.03278 0.02179 -0.0606 0.8669 0.2096
-3.750 -0.2060 0.03218 0.02105 -0.0620 0.8612 0.2237
-3.500 -0.1853 0.03186 0.02065 -0.0609 0.8508 0.2352
-3.250 -0.1479 0.03131 0.02006 -0.0625 0.8454 0.2508
-3.000 -0.1272 0.03106 0.01978 -0.0614 0.8349 0.2638
-2.750 -0.0900 0.03056 0.01923 -0.0630 0.8291 0.2828
-2.500 -0.0661 0.03035 0.01899 -0.0624 0.8193 0.3001
-2.250 -0.0318 0.02989 0.01854 -0.0634 0.8127 0.3229
-2.000 -0.0057 0.02964 0.01830 -0.0631 0.8041 0.3465
-1.750 0.0241 0.02926 0.01799 -0.0633 0.7964 0.3746
-1.500 0.0634 0.02858 0.01747 -0.0650 0.7921 0.4142
-1.250 0.0778 0.02858 0.01762 -0.0627 0.7802 0.4491
-1.000 0.1137 0.02786 0.01724 -0.0635 0.7754 0.5160
-0.750 0.1283 0.02776 0.01750 -0.0609 0.7642 0.5923
-0.500 0.1727 0.02704 0.01735 -0.0625 0.7594 0.7471
-0.250 0.3247 0.02666 0.01707 -0.0851 0.7592 0.9868
0.000 0.3448 0.02695 0.01714 -0.0841 0.7487 1.0000
0.250 0.3768 0.02684 0.01681 -0.0847 0.7416 1.0000
0.500 0.3903 0.02714 0.01694 -0.0824 0.7306 1.0000
0.750 0.4236 0.02702 0.01664 -0.0831 0.7237 1.0000
1.000 0.4364 0.02741 0.01690 -0.0806 0.7128 1.0000
1.250 0.4697 0.02730 0.01664 -0.0812 0.7060 1.0000
1.500 0.4826 0.02774 0.01698 -0.0787 0.6953 1.0000
1.750 0.5148 0.02769 0.01680 -0.0792 0.6885 1.0000
2.000 0.5283 0.02817 0.01719 -0.0768 0.6782 1.0000
2.250 0.5595 0.02815 0.01708 -0.0770 0.6710 1.0000
2.500 0.5740 0.02865 0.01750 -0.0749 0.6613 1.0000
2.750 0.6032 0.02870 0.01747 -0.0748 0.6537 1.0000
3.000 0.6199 0.02917 0.01788 -0.0729 0.6445 1.0000
3.500 0.6664 0.02971 0.01832 -0.0711 0.6281 1.0000
3.750 0.6877 0.03005 0.01863 -0.0699 0.6194 1.0000
4.000 0.7140 0.03026 0.01880 -0.0695 0.6118 1.0000
4.250 0.7282 0.03083 0.01934 -0.0673 0.6022 1.0000
4.500 0.7629 0.03079 0.01927 -0.0680 0.5957 1.0000
4.750 0.7674 0.03167 0.02016 -0.0644 0.5850 1.0000
5.000 0.8110 0.03134 0.01979 -0.0664 0.5793 1.0000
5.250 0.8055 0.03256 0.02104 -0.0615 0.5677 1.0000
5.500 0.8534 0.03209 0.02055 -0.0640 0.5619 1.0000
5.750 0.8427 0.03349 0.02199 -0.0584 0.5501 1.0000
6.000 0.8882 0.03305 0.02153 -0.0605 0.5438 1.0000
6.250 0.8788 0.03446 0.02299 -0.0552 0.5323 1.0000
6.500 0.9159 0.03424 0.02278 -0.0561 0.5250 1.0000
6.750 0.9140 0.03544 0.02404 -0.0519 0.5141 1.0000
7.000 0.9392 0.03563 0.02424 -0.0512 0.5057 1.0000
7.250 0.9495 0.03638 0.02504 -0.0487 0.4955 1.0000
7.500 0.9606 0.03713 0.02583 -0.0464 0.4856 1.0000
7.750 0.9879 0.03710 0.02582 -0.0458 0.4764 1.0000
8.000 0.9851 0.03850 0.02729 -0.0421 0.4651 1.0000
8.250 1.0298 0.03758 0.02636 -0.0432 0.4567 1.0000
8.500 1.0145 0.03961 0.02849 -0.0384 0.4447 1.0000
8.750 1.0299 0.04014 0.02906 -0.0366 0.4347 1.0000
9.000 1.0485 0.04046 0.02943 -0.0352 0.4245 1.0000
9.250 1.0431 0.04227 0.03133 -0.0319 0.4131 1.0000
9.500 1.0767 0.04168 0.03072 -0.0317 0.4040 1.0000
9.750 1.0673 0.04381 0.03297 -0.0284 0.3923 1.0000
10.000 1.0710 0.04522 0.03446 -0.0262 0.3817 1.0000
10.250 1.0986 0.04490 0.03414 -0.0254 0.3722 1.0000
10.500 1.0849 0.04770 0.03707 -0.0226 0.3605 1.0000
10.750 1.0986 0.04846 0.03786 -0.0212 0.3506 1.0000
11.000 1.1098 0.04938 0.03883 -0.0197 0.3402 1.0000
11.250 1.1006 0.05221 0.04177 -0.0177 0.3292 1.0000
11.500 1.1259 0.05194 0.04149 -0.0167 0.3200 1.0000
11.750 1.1158 0.05500 0.04467 -0.0151 0.3093 1.0000
12.000 1.1165 0.05717 0.04691 -0.0138 0.2995 1.0000
12.250 1.1360 0.05741 0.04717 -0.0127 0.2906 1.0000
12.750 1.1489 0.06069 0.05052 -0.0105 0.2724 1.0000
13.000 1.1212 0.06635 0.05638 -0.0101 0.2628 1.0000
13.250 1.1400 0.06663 0.05665 -0.0090 0.2549 1.0000
13.500 1.1211 0.07162 0.06177 -0.0089 0.2461 1.0000
13.750 1.1323 0.07285 0.06305 -0.0081 0.2386 1.0000
14.250 1.1219 0.07979 0.07014 -0.0080 0.2231 1.0000
14.500 1.0898 0.08751 0.07802 -0.0096 0.2150 1.0000
14.750 1.1097 0.08735 0.07786 -0.0085 0.2083 1.0000
15.000 1.0516 0.09998 0.09067 -0.0127 0.1996 1.0000
15.250 1.0943 0.09574 0.08640 -0.0099 0.1939 1.0000
15.500 1.0144 0.11338 0.10419 -0.0169 0.1842 1.0000
15.750 1.0935 0.10198 0.09275 -0.0107 0.1803 1.0000
16.000 0.9867 0.12583 0.11675 -0.0214 0.1693 1.0000
16.250 1.0486 0.11666 0.10763 -0.0160 0.1665 1.0000
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