NACA 2414 (n2414-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2414 (n2414-il) Reynolds number: 50,000 Max Cl/Cd: 32.74 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2414-il-50000-n5.txt Download as CSV file: xf-n2414-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2414
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7130 0.06362 0.05514 -0.0612 1.0000 0.0845
-10.500 -0.7230 0.06091 0.05240 -0.0594 1.0000 0.0855
-10.250 -0.7314 0.05824 0.04965 -0.0575 1.0000 0.0867
-10.000 -0.7390 0.05561 0.04689 -0.0554 1.0000 0.0883
-9.750 -0.7481 0.05272 0.04381 -0.0529 1.0000 0.0901
-9.500 -0.7564 0.04965 0.04042 -0.0502 1.0000 0.0921
-9.250 -0.7629 0.04646 0.03676 -0.0474 1.0000 0.0943
-9.000 -0.7538 0.04476 0.03501 -0.0454 1.0000 0.0967
-8.750 -0.7435 0.04334 0.03354 -0.0435 1.0000 0.0998
-8.500 -0.7360 0.04142 0.03136 -0.0413 1.0000 0.1035
-8.250 -0.7280 0.03930 0.02886 -0.0391 1.0000 0.1072
-8.000 -0.7134 0.03826 0.02790 -0.0374 1.0000 0.1109
-7.750 -0.7004 0.03689 0.02635 -0.0356 1.0000 0.1157
-7.500 -0.6867 0.03538 0.02459 -0.0338 1.0000 0.1208
-7.250 -0.6711 0.03446 0.02371 -0.0322 1.0000 0.1259
-7.000 -0.6555 0.03321 0.02216 -0.0306 1.0000 0.1328
-6.750 -0.6390 0.03233 0.02138 -0.0291 1.0000 0.1387
-6.500 -0.6220 0.03136 0.02019 -0.0276 1.0000 0.1470
-6.250 -0.6047 0.03057 0.01949 -0.0262 1.0000 0.1544
-6.000 -0.5866 0.02975 0.01852 -0.0249 1.0000 0.1643
-5.750 -0.5687 0.02909 0.01789 -0.0236 1.0000 0.1739
-5.500 -0.5503 0.02844 0.01724 -0.0224 1.0000 0.1849
-5.250 -0.5312 0.02784 0.01659 -0.0213 1.0000 0.1977
-5.000 -0.5119 0.02733 0.01604 -0.0202 1.0000 0.2122
-4.750 -0.4924 0.02687 0.01561 -0.0193 1.0000 0.2275
-4.500 -0.4659 0.02643 0.01521 -0.0197 0.9973 0.2466
-4.250 -0.4278 0.02601 0.01488 -0.0223 0.9897 0.2711
-4.000 -0.3882 0.02564 0.01454 -0.0251 0.9822 0.3003
-3.750 -0.3517 0.02526 0.01423 -0.0273 0.9731 0.3311
-3.500 -0.3158 0.02490 0.01399 -0.0293 0.9642 0.3644
-3.250 -0.2775 0.02457 0.01379 -0.0317 0.9559 0.4030
-2.750 -0.2108 0.02396 0.01355 -0.0340 0.9361 0.4884
-2.500 -0.1769 0.02370 0.01349 -0.0351 0.9264 0.5393
-2.250 -0.1469 0.02348 0.01348 -0.0351 0.9156 0.5920
-2.000 -0.1101 0.02329 0.01350 -0.0361 0.9076 0.6509
-1.750 -0.0829 0.02319 0.01357 -0.0352 0.8956 0.7051
-1.500 -0.0469 0.02314 0.01365 -0.0356 0.8869 0.7621
-1.250 -0.0102 0.02317 0.01374 -0.0362 0.8768 0.8155
-1.000 0.0334 0.02323 0.01380 -0.0382 0.8675 0.8650
-0.750 0.0874 0.02328 0.01378 -0.0424 0.8589 0.9071
-0.500 0.1447 0.02330 0.01369 -0.0476 0.8497 0.9420
-0.250 0.2093 0.02318 0.01347 -0.0544 0.8410 0.9698
0.000 0.2733 0.02301 0.01321 -0.0616 0.8305 0.9934
0.250 0.3149 0.02272 0.01282 -0.0644 0.8193 1.0000
0.500 0.3356 0.02264 0.01265 -0.0633 0.8043 1.0000
0.750 0.3564 0.02262 0.01255 -0.0622 0.7892 1.0000
1.000 0.3784 0.02262 0.01247 -0.0612 0.7748 1.0000
1.250 0.4025 0.02260 0.01237 -0.0604 0.7612 1.0000
1.500 0.4307 0.02250 0.01218 -0.0601 0.7494 1.0000
1.750 0.4514 0.02262 0.01225 -0.0587 0.7343 1.0000
2.000 0.4729 0.02276 0.01233 -0.0575 0.7199 1.0000
2.250 0.4961 0.02287 0.01239 -0.0564 0.7062 1.0000
2.500 0.5217 0.02293 0.01238 -0.0556 0.6934 1.0000
2.750 0.5463 0.02303 0.01244 -0.0547 0.6800 1.0000
3.000 0.5676 0.02326 0.01265 -0.0534 0.6654 1.0000
3.250 0.5902 0.02348 0.01285 -0.0522 0.6514 1.0000
3.500 0.6144 0.02366 0.01300 -0.0512 0.6379 1.0000
3.750 0.6409 0.02378 0.01306 -0.0505 0.6250 1.0000
4.000 0.6627 0.02406 0.01335 -0.0493 0.6102 1.0000
4.250 0.6845 0.02437 0.01368 -0.0480 0.5954 1.0000
4.500 0.7072 0.02467 0.01398 -0.0468 0.5809 1.0000
4.750 0.7306 0.02494 0.01424 -0.0457 0.5665 1.0000
5.000 0.7546 0.02519 0.01449 -0.0447 0.5520 1.0000
5.250 0.7789 0.02543 0.01471 -0.0437 0.5372 1.0000
5.500 0.8000 0.02579 0.01510 -0.0423 0.5211 1.0000
5.750 0.8208 0.02616 0.01551 -0.0409 0.5048 1.0000
6.000 0.8415 0.02654 0.01590 -0.0395 0.4880 1.0000
6.250 0.8618 0.02692 0.01631 -0.0380 0.4710 1.0000
6.500 0.8817 0.02732 0.01673 -0.0364 0.4535 1.0000
6.750 0.9009 0.02774 0.01717 -0.0348 0.4356 1.0000
7.000 0.9195 0.02817 0.01761 -0.0331 0.4173 1.0000
7.250 0.9374 0.02863 0.01806 -0.0313 0.3986 1.0000
7.500 0.9531 0.02918 0.01864 -0.0293 0.3791 1.0000
7.750 0.9676 0.02979 0.01929 -0.0272 0.3591 1.0000
8.000 0.9814 0.03044 0.01995 -0.0251 0.3390 1.0000
8.250 0.9945 0.03114 0.02063 -0.0229 0.3192 1.0000
8.500 1.0067 0.03192 0.02137 -0.0207 0.3000 1.0000
8.750 1.0175 0.03279 0.02217 -0.0184 0.2814 1.0000
9.000 1.0266 0.03380 0.02316 -0.0160 0.2631 1.0000
9.250 1.0335 0.03489 0.02422 -0.0134 0.2462 1.0000
9.500 1.0400 0.03609 0.02540 -0.0110 0.2304 1.0000
9.750 1.0462 0.03740 0.02666 -0.0087 0.2157 1.0000
10.000 1.0522 0.03883 0.02808 -0.0066 0.2021 1.0000
10.250 1.0580 0.04041 0.02969 -0.0047 0.1892 1.0000
10.500 1.0638 0.04207 0.03139 -0.0029 0.1776 1.0000
10.750 1.0696 0.04378 0.03308 -0.0013 0.1676 1.0000
11.000 1.0754 0.04556 0.03487 0.0001 0.1583 1.0000
11.250 1.0806 0.04754 0.03696 0.0014 0.1495 1.0000
11.500 1.0878 0.04930 0.03862 0.0026 0.1423 1.0000
11.750 1.0913 0.05162 0.04115 0.0036 0.1349 1.0000
12.000 1.0990 0.05343 0.04289 0.0046 0.1288 1.0000
12.250 1.1009 0.05608 0.04579 0.0054 0.1229 1.0000
12.500 1.1060 0.05828 0.04802 0.0062 0.1177 1.0000
12.750 1.1099 0.06078 0.05061 0.0068 0.1131 1.0000
13.000 1.1085 0.06392 0.05398 0.0071 0.1089 1.0000
13.250 1.1127 0.06636 0.05647 0.0075 0.1051 1.0000
13.500 1.1144 0.06927 0.05947 0.0077 0.1017 1.0000
13.750 1.1031 0.07384 0.06435 0.0071 0.0990 1.0000
14.000 1.0939 0.07828 0.06901 0.0063 0.0965 1.0000
14.250 1.0908 0.08192 0.07274 0.0057 0.0940 1.0000
14.500 1.0963 0.08445 0.07525 0.0058 0.0913 1.0000
14.750 1.0668 0.09229 0.08343 0.0025 0.0904 1.0000
15.000 1.0281 0.10248 0.09394 -0.0026 0.0899 1.0000
15.250 0.9623 0.11971 0.11147 -0.0125 0.0901 1.0000
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