NACA 2414 (n2414-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2414 (n2414-il) Reynolds number: 200,000 Max Cl/Cd: 65.07 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n2414-il-200000.txt Download as CSV file: xf-n2414-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7757 0.07662 0.07216 -0.0588 1.0000 0.0507
-13.500 -0.8145 0.06684 0.06220 -0.0661 1.0000 0.0504
-13.250 -0.8486 0.05934 0.05449 -0.0712 1.0000 0.0501
-13.000 -0.8784 0.05381 0.04871 -0.0735 1.0000 0.0500
-12.750 -0.9045 0.04976 0.04441 -0.0730 1.0000 0.0501
-12.500 -0.9282 0.04681 0.04122 -0.0699 1.0000 0.0502
-12.250 -0.9473 0.04424 0.03837 -0.0659 1.0000 0.0504
-12.000 -0.9610 0.04191 0.03571 -0.0620 1.0000 0.0508
-11.750 -0.9600 0.03940 0.03309 -0.0595 1.0000 0.0515
-11.500 -0.9502 0.03806 0.03175 -0.0575 1.0000 0.0524
-11.250 -0.9413 0.03695 0.03060 -0.0552 1.0000 0.0535
-11.000 -0.9344 0.03568 0.02922 -0.0526 1.0000 0.0546
-10.750 -0.9298 0.03418 0.02750 -0.0496 1.0000 0.0558
-10.500 -0.9254 0.03267 0.02568 -0.0465 1.0000 0.0570
-10.250 -0.9184 0.03104 0.02379 -0.0436 1.0000 0.0581
-10.000 -0.9038 0.02973 0.02253 -0.0419 1.0000 0.0595
-9.750 -0.8901 0.02887 0.02164 -0.0399 1.0000 0.0610
-9.500 -0.8769 0.02799 0.02064 -0.0377 1.0000 0.0630
-9.250 -0.8640 0.02710 0.01951 -0.0354 1.0000 0.0650
-9.000 -0.8488 0.02582 0.01819 -0.0337 1.0000 0.0669
-8.750 -0.8323 0.02510 0.01750 -0.0320 1.0000 0.0690
-8.500 -0.8160 0.02440 0.01671 -0.0303 1.0000 0.0715
-8.250 -0.7994 0.02381 0.01592 -0.0285 1.0000 0.0741
-8.000 -0.7818 0.02279 0.01498 -0.0272 1.0000 0.0770
-7.750 -0.7636 0.02227 0.01445 -0.0258 1.0000 0.0801
-7.500 -0.7448 0.02182 0.01383 -0.0244 1.0000 0.0836
-7.250 -0.7258 0.02100 0.01310 -0.0233 1.0000 0.0874
-7.000 -0.7013 0.02057 0.01264 -0.0231 0.9991 0.0922
-6.750 -0.6627 0.01983 0.01192 -0.0257 0.9952 0.0986
-6.500 -0.6233 0.01944 0.01144 -0.0283 0.9910 0.1061
-6.250 -0.5855 0.01877 0.01087 -0.0307 0.9862 0.1146
-6.000 -0.5443 0.01822 0.01035 -0.0338 0.9826 0.1249
-5.750 -0.5092 0.01773 0.00987 -0.0355 0.9762 0.1360
-5.500 -0.4689 0.01728 0.00946 -0.0382 0.9717 0.1497
-5.250 -0.4320 0.01684 0.00908 -0.0403 0.9663 0.1650
-5.000 -0.3955 0.01638 0.00872 -0.0422 0.9603 0.1824
-4.750 -0.3540 0.01594 0.00839 -0.0452 0.9566 0.2037
-4.500 -0.3210 0.01559 0.00810 -0.0463 0.9492 0.2255
-4.250 -0.2822 0.01516 0.00779 -0.0486 0.9441 0.2509
-4.000 -0.2384 0.01475 0.00748 -0.0519 0.9410 0.2812
-3.750 -0.2077 0.01438 0.00726 -0.0525 0.9325 0.3081
-3.500 -0.1689 0.01395 0.00695 -0.0546 0.9275 0.3408
-3.250 -0.1287 0.01348 0.00662 -0.0570 0.9240 0.3769
-3.000 -0.1026 0.01314 0.00642 -0.0564 0.9133 0.4105
-2.750 -0.0668 0.01264 0.00613 -0.0577 0.9081 0.4541
-2.500 -0.0410 0.01231 0.00597 -0.0570 0.8974 0.4985
-2.250 -0.0087 0.01187 0.00572 -0.0574 0.8909 0.5505
-2.000 0.0157 0.01157 0.00562 -0.0562 0.8791 0.5989
-1.750 0.0447 0.01123 0.00545 -0.0557 0.8708 0.6490
-1.500 0.0699 0.01099 0.00535 -0.0545 0.8589 0.6952
-1.250 0.0953 0.01080 0.00529 -0.0532 0.8470 0.7387
-1.000 0.1227 0.01061 0.00518 -0.0522 0.8367 0.7793
-0.750 0.1476 0.01052 0.00516 -0.0507 0.8231 0.8165
-0.500 0.1732 0.01049 0.00517 -0.0493 0.8094 0.8507
-0.250 0.2011 0.01051 0.00518 -0.0483 0.7962 0.8807
0.000 0.2322 0.01056 0.00517 -0.0480 0.7831 0.9063
0.250 0.2667 0.01065 0.00519 -0.0486 0.7685 0.9275
0.500 0.3046 0.01077 0.00523 -0.0500 0.7529 0.9451
0.750 0.3467 0.01089 0.00526 -0.0525 0.7371 0.9592
1.000 0.3925 0.01100 0.00527 -0.0558 0.7208 0.9709
1.250 0.4388 0.01109 0.00526 -0.0594 0.7041 0.9820
1.500 0.4880 0.01115 0.00521 -0.0638 0.6869 0.9910
1.750 0.5369 0.01119 0.00516 -0.0682 0.6695 0.9997
2.000 0.5600 0.01123 0.00510 -0.0675 0.6544 1.0000
2.250 0.5821 0.01130 0.00508 -0.0665 0.6399 1.0000
2.500 0.6043 0.01140 0.00507 -0.0655 0.6258 1.0000
2.750 0.6259 0.01150 0.00512 -0.0644 0.6109 1.0000
3.000 0.6477 0.01162 0.00519 -0.0632 0.5965 1.0000
3.250 0.6696 0.01176 0.00527 -0.0621 0.5825 1.0000
3.500 0.6916 0.01192 0.00535 -0.0609 0.5687 1.0000
3.750 0.7137 0.01210 0.00544 -0.0597 0.5550 1.0000
4.000 0.7351 0.01226 0.00558 -0.0585 0.5404 1.0000
4.250 0.7567 0.01243 0.00572 -0.0572 0.5259 1.0000
4.500 0.7784 0.01263 0.00587 -0.0559 0.5116 1.0000
4.750 0.8000 0.01284 0.00603 -0.0547 0.4971 1.0000
5.000 0.8215 0.01306 0.00619 -0.0533 0.4824 1.0000
5.250 0.8426 0.01329 0.00635 -0.0520 0.4671 1.0000
5.500 0.8636 0.01350 0.00655 -0.0506 0.4510 1.0000
5.750 0.8845 0.01373 0.00676 -0.0492 0.4344 1.0000
6.000 0.9053 0.01398 0.00697 -0.0478 0.4174 1.0000
6.250 0.9258 0.01425 0.00721 -0.0464 0.3995 1.0000
6.500 0.9461 0.01455 0.00745 -0.0449 0.3810 1.0000
6.750 0.9663 0.01485 0.00773 -0.0435 0.3611 1.0000
7.000 0.9861 0.01519 0.00804 -0.0420 0.3403 1.0000
7.250 1.0051 0.01560 0.00838 -0.0405 0.3189 1.0000
7.500 1.0230 0.01608 0.00876 -0.0388 0.2974 1.0000
7.750 1.0412 0.01656 0.00919 -0.0372 0.2743 1.0000
8.000 1.0578 0.01714 0.00967 -0.0354 0.2516 1.0000
8.250 1.0738 0.01777 0.01021 -0.0336 0.2293 1.0000
8.500 1.0891 0.01844 0.01080 -0.0316 0.2076 1.0000
8.750 1.1026 0.01922 0.01146 -0.0295 0.1880 1.0000
9.000 1.1149 0.02005 0.01219 -0.0272 0.1707 1.0000
9.250 1.1258 0.02087 0.01294 -0.0247 0.1556 1.0000
9.500 1.1355 0.02177 0.01377 -0.0221 0.1426 1.0000
9.750 1.1468 0.02265 0.01464 -0.0198 0.1311 1.0000
10.000 1.1575 0.02361 0.01561 -0.0176 0.1213 1.0000
10.250 1.1659 0.02475 0.01669 -0.0153 0.1134 1.0000
10.500 1.1766 0.02577 0.01773 -0.0133 0.1061 1.0000
10.750 1.1857 0.02699 0.01895 -0.0113 0.1000 1.0000
11.000 1.1956 0.02813 0.02011 -0.0095 0.0944 1.0000
11.250 1.2040 0.02951 0.02148 -0.0077 0.0897 1.0000
11.500 1.2142 0.03072 0.02275 -0.0061 0.0851 1.0000
11.750 1.2216 0.03231 0.02424 -0.0045 0.0813 1.0000
12.000 1.2318 0.03358 0.02568 -0.0031 0.0777 1.0000
12.250 1.2408 0.03499 0.02712 -0.0019 0.0745 1.0000
12.500 1.2502 0.03664 0.02867 -0.0005 0.0715 1.0000
12.750 1.2583 0.03816 0.03038 0.0006 0.0689 1.0000
13.000 1.2666 0.03974 0.03202 0.0017 0.0663 1.0000
13.250 1.2759 0.04133 0.03357 0.0027 0.0641 1.0000
13.500 1.2852 0.04309 0.03540 0.0037 0.0620 1.0000
13.750 1.2909 0.04498 0.03745 0.0046 0.0600 1.0000
14.000 1.2975 0.04682 0.03936 0.0054 0.0581 1.0000
14.250 1.3071 0.04848 0.04099 0.0061 0.0564 1.0000
14.500 1.3165 0.05043 0.04299 0.0070 0.0548 1.0000
14.750 1.3182 0.05285 0.04562 0.0076 0.0536 1.0000
15.000 1.3203 0.05529 0.04822 0.0081 0.0523 1.0000
15.250 1.3233 0.05764 0.05067 0.0084 0.0510 1.0000
15.500 1.3295 0.05971 0.05275 0.0088 0.0498 1.0000
15.750 1.3432 0.06147 0.05446 0.0096 0.0484 1.0000
16.000 1.3345 0.06506 0.05831 0.0094 0.0477 1.0000
16.250 1.3264 0.06881 0.06230 0.0090 0.0470 1.0000
16.500 1.3193 0.07264 0.06634 0.0083 0.0463 1.0000
16.750 1.3127 0.07655 0.07042 0.0075 0.0456 1.0000
17.000 1.3058 0.08059 0.07463 0.0065 0.0449 1.0000
17.250 1.2979 0.08487 0.07907 0.0052 0.0444 1.0000
17.500 1.2907 0.08916 0.08349 0.0038 0.0439 1.0000
17.750 1.2871 0.09299 0.08740 0.0026 0.0433 1.0000
18.000 1.2906 0.09583 0.09025 0.0024 0.0426 1.0000
18.250 1.2731 0.10199 0.09660 -0.0002 0.0423 1.0000
18.500 1.2472 0.10983 0.10470 -0.0045 0.0423 1.0000
18.750 1.2181 0.11873 0.11386 -0.0099 0.0422 1.0000
19.000 1.1853 0.12890 0.12428 -0.0163 0.0423 1.0000
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Polar data table (+)
Polar graphs
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