NACA 2414 (n2414-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2414 (n2414-il) Reynolds number: 200,000 Max Cl/Cd: 62.15 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2414-il-200000-n5.txt Download as CSV file: xf-n2414-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8947 0.08030 0.07530 -0.0498 1.0000 0.0312
-15.250 -0.9230 0.07161 0.06639 -0.0556 1.0000 0.0313
-15.000 -0.9424 0.06473 0.05934 -0.0601 1.0000 0.0314
-14.750 -0.9567 0.05893 0.05336 -0.0640 1.0000 0.0317
-14.500 -0.9674 0.05394 0.04821 -0.0672 1.0000 0.0319
-14.250 -0.9754 0.04964 0.04374 -0.0697 1.0000 0.0322
-14.000 -0.9813 0.04594 0.03987 -0.0714 1.0000 0.0326
-13.750 -0.9854 0.04276 0.03652 -0.0724 1.0000 0.0331
-13.500 -0.9881 0.04005 0.03361 -0.0727 1.0000 0.0336
-13.250 -0.9897 0.03773 0.03109 -0.0722 1.0000 0.0341
-13.000 -0.9886 0.03594 0.02922 -0.0711 1.0000 0.0346
-12.750 -0.9863 0.03452 0.02776 -0.0694 1.0000 0.0351
-12.500 -0.9846 0.03332 0.02650 -0.0670 1.0000 0.0357
-12.250 -0.9837 0.03228 0.02539 -0.0640 1.0000 0.0363
-12.000 -0.9796 0.03124 0.02426 -0.0612 1.0000 0.0370
-11.750 -0.9740 0.03022 0.02313 -0.0585 1.0000 0.0379
-11.500 -0.9670 0.02922 0.02199 -0.0558 1.0000 0.0387
-11.250 -0.9593 0.02827 0.02095 -0.0531 1.0000 0.0395
-11.000 -0.9506 0.02745 0.02011 -0.0505 1.0000 0.0403
-10.750 -0.9405 0.02671 0.01933 -0.0480 1.0000 0.0412
-10.500 -0.9295 0.02600 0.01855 -0.0456 1.0000 0.0424
-10.250 -0.9177 0.02529 0.01774 -0.0432 1.0000 0.0437
-10.000 -0.9055 0.02457 0.01693 -0.0409 1.0000 0.0450
-9.750 -0.8930 0.02391 0.01626 -0.0387 1.0000 0.0462
-9.500 -0.8791 0.02331 0.01562 -0.0366 1.0000 0.0476
-9.250 -0.8483 0.02257 0.01478 -0.0378 0.9970 0.0498
-9.000 -0.8171 0.02183 0.01399 -0.0392 0.9940 0.0521
-8.750 -0.7867 0.02120 0.01332 -0.0403 0.9904 0.0546
-8.500 -0.7552 0.02061 0.01262 -0.0415 0.9867 0.0576
-8.250 -0.7228 0.01996 0.01199 -0.0430 0.9836 0.0606
-8.000 -0.6917 0.01944 0.01140 -0.0440 0.9797 0.0642
-7.750 -0.6612 0.01886 0.01081 -0.0450 0.9751 0.0678
-7.500 -0.6276 0.01837 0.01028 -0.0465 0.9717 0.0724
-7.250 -0.5946 0.01785 0.00976 -0.0479 0.9682 0.0771
-7.000 -0.5650 0.01742 0.00929 -0.0484 0.9624 0.0825
-6.750 -0.5310 0.01693 0.00881 -0.0499 0.9586 0.0885
-6.500 -0.4949 0.01649 0.00834 -0.0518 0.9556 0.0957
-6.250 -0.4678 0.01608 0.00796 -0.0518 0.9480 0.1030
-6.000 -0.4349 0.01566 0.00755 -0.0529 0.9430 0.1116
-5.750 -0.4031 0.01529 0.00717 -0.0538 0.9375 0.1213
-5.500 -0.3747 0.01494 0.00684 -0.0539 0.9298 0.1320
-5.250 -0.3419 0.01455 0.00650 -0.0550 0.9247 0.1447
-5.000 -0.3152 0.01423 0.00622 -0.0547 0.9159 0.1574
-4.750 -0.2845 0.01390 0.00592 -0.0553 0.9094 0.1722
-4.500 -0.2564 0.01360 0.00567 -0.0553 0.9010 0.1878
-4.250 -0.2270 0.01330 0.00541 -0.0555 0.8930 0.2050
-4.000 -0.1990 0.01303 0.00519 -0.0555 0.8841 0.2233
-3.750 -0.1700 0.01276 0.00496 -0.0556 0.8753 0.2433
-3.500 -0.1425 0.01253 0.00477 -0.0554 0.8652 0.2637
-3.250 -0.1137 0.01226 0.00456 -0.0554 0.8559 0.2860
-3.000 -0.0871 0.01204 0.00440 -0.0551 0.8445 0.3088
-2.750 -0.0592 0.01183 0.00423 -0.0549 0.8338 0.3335
-2.500 -0.0320 0.01160 0.00407 -0.0546 0.8221 0.3599
-2.000 0.0214 0.01120 0.00383 -0.0538 0.7973 0.4208
-1.500 0.0740 0.01083 0.00365 -0.0528 0.7709 0.4980
-1.250 0.0998 0.01066 0.00360 -0.0521 0.7570 0.5394
-1.000 0.1257 0.01052 0.00356 -0.0515 0.7432 0.5806
-0.750 0.1515 0.01041 0.00353 -0.0508 0.7291 0.6210
-0.500 0.1773 0.01033 0.00352 -0.0500 0.7148 0.6604
-0.250 0.2028 0.01026 0.00353 -0.0491 0.6999 0.6985
0.000 0.2283 0.01022 0.00356 -0.0483 0.6854 0.7353
0.250 0.2539 0.01021 0.00360 -0.0474 0.6709 0.7712
0.500 0.2799 0.01023 0.00366 -0.0465 0.6569 0.8056
0.750 0.3066 0.01029 0.00372 -0.0458 0.6426 0.8377
1.000 0.3345 0.01038 0.00381 -0.0454 0.6280 0.8676
1.250 0.3649 0.01049 0.00390 -0.0455 0.6136 0.8932
1.500 0.3965 0.01063 0.00398 -0.0459 0.5993 0.9156
1.750 0.4295 0.01077 0.00407 -0.0467 0.5851 0.9342
2.000 0.4639 0.01093 0.00416 -0.0479 0.5708 0.9496
2.250 0.4993 0.01110 0.00425 -0.0494 0.5564 0.9629
2.500 0.5356 0.01125 0.00435 -0.0511 0.5419 0.9745
2.750 0.5747 0.01142 0.00446 -0.0535 0.5274 0.9849
3.000 0.6169 0.01160 0.00458 -0.0565 0.5125 0.9946
3.250 0.6524 0.01176 0.00468 -0.0583 0.4981 1.0000
3.750 0.6952 0.01208 0.00488 -0.0558 0.4713 1.0000
4.000 0.7168 0.01225 0.00502 -0.0546 0.4578 1.0000
4.250 0.7382 0.01245 0.00516 -0.0534 0.4443 1.0000
4.500 0.7594 0.01266 0.00531 -0.0521 0.4300 1.0000
4.750 0.7805 0.01288 0.00548 -0.0508 0.4150 1.0000
5.000 0.8017 0.01311 0.00566 -0.0495 0.3991 1.0000
5.250 0.8226 0.01335 0.00586 -0.0481 0.3824 1.0000
5.500 0.8434 0.01363 0.00608 -0.0468 0.3648 1.0000
5.750 0.8642 0.01392 0.00631 -0.0455 0.3467 1.0000
6.000 0.8850 0.01424 0.00657 -0.0442 0.3277 1.0000
6.250 0.9054 0.01459 0.00686 -0.0429 0.3079 1.0000
6.500 0.9256 0.01498 0.00718 -0.0416 0.2879 1.0000
6.750 0.9452 0.01541 0.00752 -0.0402 0.2679 1.0000
7.000 0.9645 0.01588 0.00790 -0.0388 0.2484 1.0000
7.250 0.9840 0.01635 0.00831 -0.0375 0.2291 1.0000
7.500 1.0030 0.01685 0.00874 -0.0361 0.2104 1.0000
7.750 1.0214 0.01739 0.00921 -0.0346 0.1924 1.0000
8.000 1.0393 0.01797 0.00972 -0.0331 0.1753 1.0000
8.250 1.0566 0.01856 0.01025 -0.0316 0.1596 1.0000
8.500 1.0735 0.01918 0.01081 -0.0300 0.1454 1.0000
8.750 1.0898 0.01981 0.01141 -0.0283 0.1328 1.0000
9.000 1.1049 0.02045 0.01203 -0.0264 0.1219 1.0000
9.250 1.1184 0.02113 0.01268 -0.0243 0.1126 1.0000
9.500 1.1314 0.02186 0.01339 -0.0223 0.1040 1.0000
9.750 1.1454 0.02257 0.01413 -0.0204 0.0965 1.0000
10.000 1.1577 0.02340 0.01495 -0.0185 0.0902 1.0000
10.250 1.1705 0.02423 0.01580 -0.0167 0.0842 1.0000
10.500 1.1820 0.02516 0.01675 -0.0149 0.0793 1.0000
10.750 1.1937 0.02611 0.01775 -0.0132 0.0746 1.0000
11.000 1.2034 0.02722 0.01887 -0.0114 0.0709 1.0000
11.250 1.2147 0.02826 0.01999 -0.0099 0.0671 1.0000
11.500 1.2232 0.02954 0.02128 -0.0083 0.0639 1.0000
11.750 1.2322 0.03083 0.02264 -0.0069 0.0611 1.0000
12.000 1.2411 0.03217 0.02407 -0.0056 0.0583 1.0000
12.250 1.2473 0.03378 0.02571 -0.0044 0.0561 1.0000
12.500 1.2542 0.03540 0.02741 -0.0033 0.0539 1.0000
12.750 1.2613 0.03706 0.02916 -0.0024 0.0518 1.0000
13.000 1.2663 0.03896 0.03113 -0.0016 0.0500 1.0000
13.250 1.2685 0.04121 0.03341 -0.0009 0.0485 1.0000
13.500 1.2740 0.04320 0.03553 -0.0003 0.0469 1.0000
13.750 1.2780 0.04541 0.03784 0.0001 0.0454 1.0000
14.000 1.2805 0.04783 0.04034 0.0003 0.0441 1.0000
14.250 1.2810 0.05053 0.04310 0.0004 0.0430 1.0000
14.500 1.2807 0.05337 0.04601 0.0004 0.0420 1.0000
14.750 1.2825 0.05607 0.04886 0.0003 0.0408 1.0000
15.000 1.2832 0.05898 0.05188 0.0000 0.0397 1.0000
15.250 1.2827 0.06208 0.05508 -0.0004 0.0388 1.0000
15.500 1.2812 0.06541 0.05848 -0.0011 0.0380 1.0000
15.750 1.2782 0.06896 0.06209 -0.0018 0.0373 1.0000
16.000 1.2760 0.07248 0.06570 -0.0026 0.0366 1.0000
16.250 1.2742 0.07601 0.06938 -0.0034 0.0358 1.0000
16.500 1.2716 0.07971 0.07321 -0.0044 0.0350 1.0000
16.750 1.2685 0.08357 0.07718 -0.0056 0.0343 1.0000
17.000 1.2648 0.08756 0.08127 -0.0069 0.0337 1.0000
17.250 1.2607 0.09167 0.08546 -0.0083 0.0331 1.0000
17.500 1.2561 0.09589 0.08975 -0.0098 0.0326 1.0000
17.750 1.2522 0.09999 0.09389 -0.0113 0.0321 1.0000
18.000 1.2466 0.10457 0.09865 -0.0132 0.0315 1.0000
18.250 1.2406 0.10926 0.10349 -0.0152 0.0309 1.0000
18.500 1.2343 0.11407 0.10843 -0.0173 0.0304 1.0000
18.750 1.2280 0.11896 0.11344 -0.0196 0.0299 1.0000
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