NACA 2415 (n2415-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2415 (n2415-il) Reynolds number: 100,000 Max Cl/Cd: 46.59 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n2415-il-100000.txt Download as CSV file: xf-n2415-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6507 0.07798 0.07213 -0.0617 1.0000 0.1023
-11.500 -0.6802 0.07054 0.06463 -0.0652 1.0000 0.1016
-11.250 -0.7174 0.06446 0.05847 -0.0663 1.0000 0.1008
-11.000 -0.7559 0.06033 0.05425 -0.0633 1.0000 0.1002
-10.750 -0.7902 0.05646 0.05019 -0.0593 1.0000 0.0999
-10.500 -0.8179 0.05276 0.04623 -0.0550 1.0000 0.1001
-10.250 -0.8397 0.04933 0.04246 -0.0505 1.0000 0.1007
-10.000 -0.8564 0.04619 0.03887 -0.0461 1.0000 0.1017
-9.750 -0.8595 0.04342 0.03584 -0.0428 1.0000 0.1032
-9.500 -0.8450 0.04206 0.03458 -0.0411 1.0000 0.1055
-9.250 -0.8361 0.04057 0.03300 -0.0388 1.0000 0.1081
-9.000 -0.8320 0.03863 0.03076 -0.0359 1.0000 0.1109
-8.750 -0.8294 0.03657 0.02818 -0.0327 1.0000 0.1137
-8.500 -0.8155 0.03484 0.02646 -0.0310 1.0000 0.1166
-8.250 -0.8003 0.03383 0.02543 -0.0293 1.0000 0.1204
-8.000 -0.7879 0.03250 0.02382 -0.0272 1.0000 0.1247
-7.750 -0.7732 0.03099 0.02214 -0.0255 1.0000 0.1289
-7.500 -0.7559 0.03015 0.02134 -0.0241 1.0000 0.1336
-7.250 -0.7399 0.02918 0.02007 -0.0224 1.0000 0.1395
-7.000 -0.7213 0.02811 0.01909 -0.0212 1.0000 0.1449
-6.750 -0.7031 0.02742 0.01828 -0.0199 1.0000 0.1518
-6.500 -0.6838 0.02653 0.01737 -0.0189 1.0000 0.1588
-6.250 -0.6645 0.02597 0.01675 -0.0178 1.0000 0.1672
-6.000 -0.6448 0.02527 0.01609 -0.0168 1.0000 0.1757
-5.750 -0.6254 0.02483 0.01547 -0.0158 1.0000 0.1862
-5.500 -0.6056 0.02427 0.01511 -0.0150 1.0000 0.1963
-5.250 -0.5858 0.02379 0.01464 -0.0141 1.0000 0.2081
-5.000 -0.5661 0.02343 0.01425 -0.0133 1.0000 0.2216
-4.750 -0.5279 0.02309 0.01401 -0.0159 0.9951 0.2406
-4.500 -0.4845 0.02281 0.01385 -0.0195 0.9876 0.2635
-4.250 -0.4395 0.02261 0.01366 -0.0233 0.9805 0.2910
-4.000 -0.3989 0.02228 0.01354 -0.0262 0.9718 0.3178
-3.750 -0.3591 0.02201 0.01337 -0.0290 0.9630 0.3485
-3.500 -0.3148 0.02174 0.01324 -0.0324 0.9555 0.3840
-3.250 -0.2801 0.02141 0.01313 -0.0340 0.9449 0.4178
-3.000 -0.2369 0.02111 0.01304 -0.0370 0.9374 0.4597
-2.750 -0.2030 0.02081 0.01298 -0.0382 0.9265 0.5007
-2.500 -0.1674 0.02054 0.01294 -0.0394 0.9168 0.5474
-2.250 -0.1284 0.02023 0.01289 -0.0411 0.9081 0.5999
-2.000 -0.0976 0.02003 0.01291 -0.0411 0.8971 0.6521
-1.750 -0.0560 0.01974 0.01284 -0.0426 0.8900 0.7094
-1.500 -0.0280 0.01967 0.01296 -0.0415 0.8786 0.7578
-1.250 0.0136 0.01948 0.01286 -0.0424 0.8721 0.8078
-1.000 0.0433 0.01955 0.01300 -0.0412 0.8608 0.8485
-0.750 0.0916 0.01945 0.01288 -0.0432 0.8544 0.8852
-0.500 0.1401 0.01954 0.01293 -0.0458 0.8447 0.9145
-0.250 0.2043 0.01938 0.01269 -0.0513 0.8376 0.9370
0.000 0.2751 0.01918 0.01241 -0.0586 0.8291 0.9537
0.250 0.3450 0.01880 0.01195 -0.0660 0.8189 0.9691
0.500 0.4104 0.01843 0.01151 -0.0730 0.8060 0.9846
0.750 0.4757 0.01790 0.01090 -0.0800 0.7934 0.9992
1.000 0.4986 0.01760 0.01050 -0.0793 0.7794 1.0000
1.250 0.5163 0.01750 0.01034 -0.0778 0.7635 1.0000
1.500 0.5349 0.01745 0.01022 -0.0763 0.7482 1.0000
1.750 0.5544 0.01742 0.01012 -0.0749 0.7339 1.0000
2.000 0.5761 0.01736 0.00997 -0.0736 0.7208 1.0000
2.250 0.5971 0.01737 0.00990 -0.0723 0.7070 1.0000
2.500 0.6159 0.01750 0.00999 -0.0706 0.6922 1.0000
2.750 0.6362 0.01763 0.01005 -0.0691 0.6783 1.0000
3.000 0.6588 0.01771 0.01005 -0.0679 0.6654 1.0000
3.250 0.6808 0.01782 0.01008 -0.0666 0.6519 1.0000
3.500 0.7000 0.01804 0.01028 -0.0649 0.6373 1.0000
3.750 0.7210 0.01824 0.01044 -0.0634 0.6234 1.0000
4.000 0.7441 0.01840 0.01051 -0.0622 0.6102 1.0000
4.250 0.7669 0.01857 0.01060 -0.0610 0.5965 1.0000
4.500 0.7864 0.01883 0.01088 -0.0593 0.5816 1.0000
4.750 0.8072 0.01909 0.01110 -0.0578 0.5671 1.0000
5.000 0.8292 0.01932 0.01127 -0.0564 0.5527 1.0000
5.250 0.8524 0.01952 0.01139 -0.0552 0.5384 1.0000
5.500 0.8741 0.01975 0.01156 -0.0538 0.5232 1.0000
5.750 0.8937 0.02003 0.01183 -0.0520 0.5071 1.0000
6.000 0.9138 0.02031 0.01211 -0.0504 0.4911 1.0000
6.250 0.9341 0.02059 0.01237 -0.0488 0.4748 1.0000
6.500 0.9545 0.02088 0.01262 -0.0472 0.4583 1.0000
6.750 0.9745 0.02117 0.01289 -0.0456 0.4414 1.0000
7.000 0.9941 0.02148 0.01316 -0.0439 0.4240 1.0000
7.250 1.0130 0.02179 0.01344 -0.0421 0.4061 1.0000
7.500 1.0311 0.02213 0.01375 -0.0403 0.3877 1.0000
7.750 1.0484 0.02251 0.01408 -0.0383 0.3688 1.0000
8.000 1.0649 0.02292 0.01444 -0.0363 0.3496 1.0000
8.250 1.0807 0.02341 0.01485 -0.0342 0.3303 1.0000
8.500 1.0960 0.02398 0.01531 -0.0321 0.3110 1.0000
8.750 1.1093 0.02465 0.01592 -0.0297 0.2914 1.0000
9.000 1.1215 0.02539 0.01663 -0.0273 0.2721 1.0000
9.250 1.1333 0.02621 0.01739 -0.0249 0.2538 1.0000
9.500 1.1446 0.02711 0.01822 -0.0224 0.2367 1.0000
9.750 1.1555 0.02808 0.01912 -0.0201 0.2209 1.0000
10.000 1.1664 0.02912 0.02009 -0.0177 0.2066 1.0000
10.250 1.1771 0.03020 0.02106 -0.0155 0.1938 1.0000
10.500 1.1872 0.03129 0.02209 -0.0131 0.1821 1.0000
10.750 1.1956 0.03250 0.02336 -0.0107 0.1713 1.0000
11.000 1.2077 0.03382 0.02464 -0.0089 0.1618 1.0000
11.250 1.2215 0.03505 0.02577 -0.0074 0.1529 1.0000
11.500 1.2295 0.03652 0.02738 -0.0052 0.1452 1.0000
11.750 1.2507 0.03795 0.02861 -0.0048 0.1374 1.0000
12.000 1.2531 0.03948 0.03041 -0.0021 0.1317 1.0000
12.250 1.2799 0.04099 0.03164 -0.0024 0.1247 1.0000
12.500 1.2781 0.04273 0.03374 0.0005 0.1207 1.0000
12.750 1.2876 0.04430 0.03536 0.0021 0.1159 1.0000
13.000 1.3072 0.04615 0.03716 0.0025 0.1112 1.0000
13.250 1.3049 0.04826 0.03956 0.0049 0.1080 1.0000
13.500 1.3095 0.05017 0.04158 0.0065 0.1046 1.0000
13.750 1.3345 0.05206 0.04333 0.0063 0.1005 1.0000
14.000 1.3214 0.05477 0.04640 0.0089 0.0988 1.0000
14.250 1.3119 0.05767 0.04959 0.0108 0.0969 1.0000
14.500 1.3078 0.06041 0.05251 0.0120 0.0947 1.0000
14.750 1.3125 0.06267 0.05481 0.0128 0.0924 1.0000
15.000 1.3232 0.06537 0.05750 0.0133 0.0900 1.0000
15.250 1.2974 0.06974 0.06222 0.0142 0.0894 1.0000
15.500 1.2692 0.07486 0.06766 0.0142 0.0890 1.0000
15.750 1.2373 0.08091 0.07402 0.0132 0.0887 1.0000
16.000 1.2005 0.08819 0.08160 0.0110 0.0888 1.0000
16.250 1.1568 0.09720 0.09090 0.0071 0.0892 1.0000
16.500 1.1059 0.10868 0.10263 0.0011 0.0899 1.0000
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Polar data table (+)
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