NACA 2414 (n2414-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2414 (n2414-il) Reynolds number: 500,000 Max Cl/Cd: 79.41 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2414-il-500000-n5.txt Download as CSV file: xf-n2414-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.0317 0.08950 0.08559 -0.0404 1.0000 0.0206
-17.250 -1.0560 0.08197 0.07794 -0.0445 1.0000 0.0206
-17.000 -1.0803 0.07457 0.07041 -0.0486 1.0000 0.0207
-16.750 -1.1030 0.06746 0.06316 -0.0526 1.0000 0.0208
-16.500 -1.1230 0.06070 0.05626 -0.0566 1.0000 0.0208
-16.250 -1.1389 0.05453 0.04994 -0.0604 1.0000 0.0209
-16.000 -1.1506 0.04906 0.04433 -0.0639 1.0000 0.0211
-15.750 -1.1582 0.04437 0.03950 -0.0669 1.0000 0.0212
-15.500 -1.1625 0.04041 0.03541 -0.0693 1.0000 0.0214
-15.250 -1.1638 0.03714 0.03200 -0.0709 1.0000 0.0217
-15.000 -1.1631 0.03444 0.02918 -0.0718 1.0000 0.0219
-14.750 -1.1605 0.03224 0.02685 -0.0721 1.0000 0.0221
-14.500 -1.1584 0.03028 0.02479 -0.0716 1.0000 0.0224
-14.250 -1.1559 0.02861 0.02305 -0.0705 1.0000 0.0227
-14.000 -1.1517 0.02730 0.02167 -0.0688 1.0000 0.0230
-13.750 -1.1470 0.02625 0.02055 -0.0666 1.0000 0.0233
-13.500 -1.1431 0.02539 0.01964 -0.0636 1.0000 0.0237
-13.250 -1.1367 0.02464 0.01882 -0.0608 1.0000 0.0241
-13.000 -1.1282 0.02394 0.01805 -0.0582 1.0000 0.0246
-12.750 -1.1186 0.02329 0.01733 -0.0556 1.0000 0.0251
-12.500 -1.1084 0.02269 0.01665 -0.0530 1.0000 0.0256
-12.250 -1.0987 0.02205 0.01596 -0.0502 1.0000 0.0261
-12.000 -1.0889 0.02142 0.01529 -0.0475 1.0000 0.0266
-11.750 -1.0701 0.02078 0.01461 -0.0465 0.9991 0.0272
-11.500 -1.0420 0.02013 0.01390 -0.0473 0.9971 0.0281
-11.250 -1.0129 0.01952 0.01323 -0.0481 0.9951 0.0290
-11.000 -0.9829 0.01896 0.01259 -0.0491 0.9934 0.0298
-10.750 -0.9560 0.01830 0.01191 -0.0496 0.9905 0.0308
-10.500 -0.9269 0.01776 0.01135 -0.0503 0.9878 0.0320
-10.250 -0.8964 0.01728 0.01081 -0.0513 0.9856 0.0334
-10.000 -0.8650 0.01677 0.01026 -0.0524 0.9837 0.0347
-9.750 -0.8329 0.01625 0.00972 -0.0537 0.9822 0.0362
-9.500 -0.8055 0.01582 0.00926 -0.0539 0.9780 0.0376
-9.250 -0.7751 0.01542 0.00881 -0.0547 0.9748 0.0392
-9.000 -0.7444 0.01495 0.00834 -0.0556 0.9720 0.0411
-8.750 -0.7125 0.01456 0.00792 -0.0567 0.9697 0.0434
-8.500 -0.6864 0.01421 0.00754 -0.0564 0.9639 0.0454
-8.250 -0.6574 0.01382 0.00716 -0.0568 0.9594 0.0478
-8.000 -0.6264 0.01348 0.00678 -0.0576 0.9558 0.0504
-7.750 -0.6006 0.01314 0.00645 -0.0572 0.9488 0.0533
-7.500 -0.5718 0.01282 0.00612 -0.0574 0.9429 0.0567
-7.250 -0.5444 0.01251 0.00580 -0.0574 0.9361 0.0602
-7.000 -0.5172 0.01223 0.00550 -0.0572 0.9282 0.0643
-6.750 -0.4897 0.01193 0.00521 -0.0571 0.9211 0.0687
-6.500 -0.4630 0.01169 0.00495 -0.0568 0.9126 0.0735
-6.250 -0.4358 0.01141 0.00468 -0.0567 0.9050 0.0789
-6.000 -0.4089 0.01120 0.00445 -0.0564 0.8959 0.0844
-5.750 -0.3819 0.01095 0.00420 -0.0562 0.8874 0.0914
-5.500 -0.3550 0.01074 0.00399 -0.0559 0.8775 0.0983
-5.250 -0.3279 0.01054 0.00378 -0.0557 0.8679 0.1060
-5.000 -0.3009 0.01033 0.00358 -0.0554 0.8574 0.1151
-4.750 -0.2739 0.01015 0.00340 -0.0551 0.8466 0.1248
-4.500 -0.2467 0.00998 0.00322 -0.0549 0.8358 0.1355
-4.250 -0.2197 0.00982 0.00306 -0.0547 0.8237 0.1479
-4.000 -0.1926 0.00965 0.00291 -0.0544 0.8117 0.1614
-3.750 -0.1655 0.00951 0.00277 -0.0542 0.7996 0.1756
-3.500 -0.1385 0.00937 0.00264 -0.0539 0.7863 0.1903
-3.250 -0.1113 0.00925 0.00253 -0.0537 0.7730 0.2061
-3.000 -0.0841 0.00913 0.00242 -0.0534 0.7598 0.2232
-2.750 -0.0571 0.00903 0.00233 -0.0532 0.7460 0.2411
-2.500 -0.0301 0.00894 0.00224 -0.0529 0.7316 0.2601
-2.250 -0.0029 0.00885 0.00217 -0.0527 0.7170 0.2796
-2.000 0.0242 0.00877 0.00210 -0.0525 0.7021 0.2999
-1.750 0.0512 0.00869 0.00204 -0.0522 0.6876 0.3217
-1.500 0.0782 0.00863 0.00200 -0.0520 0.6727 0.3459
-1.000 0.1318 0.00850 0.00192 -0.0514 0.6432 0.3987
-0.750 0.1586 0.00841 0.00190 -0.0512 0.6287 0.4310
-0.500 0.1852 0.00832 0.00190 -0.0509 0.6143 0.4689
-0.250 0.2118 0.00825 0.00190 -0.0505 0.6006 0.5080
0.000 0.2382 0.00820 0.00192 -0.0502 0.5866 0.5457
0.250 0.2647 0.00816 0.00194 -0.0498 0.5730 0.5817
0.500 0.2913 0.00812 0.00198 -0.0495 0.5595 0.6171
0.750 0.3178 0.00809 0.00202 -0.0491 0.5465 0.6518
1.000 0.3441 0.00809 0.00208 -0.0487 0.5339 0.6852
1.500 0.3966 0.00808 0.00221 -0.0477 0.5092 0.7530
1.750 0.4225 0.00809 0.00229 -0.0471 0.4981 0.7861
2.000 0.4481 0.00812 0.00239 -0.0465 0.4862 0.8187
2.250 0.4740 0.00816 0.00249 -0.0458 0.4750 0.8504
2.500 0.4995 0.00823 0.00260 -0.0451 0.4636 0.8801
2.750 0.5259 0.00835 0.00272 -0.0445 0.4511 0.9058
3.000 0.5542 0.00847 0.00284 -0.0444 0.4383 0.9276
3.250 0.5843 0.00862 0.00296 -0.0447 0.4251 0.9449
3.500 0.6159 0.00880 0.00309 -0.0455 0.4111 0.9588
3.750 0.6485 0.00899 0.00323 -0.0465 0.3956 0.9709
4.000 0.6836 0.00921 0.00338 -0.0480 0.3786 0.9826
4.250 0.7211 0.00945 0.00354 -0.0502 0.3589 0.9899
4.500 0.7552 0.00971 0.00371 -0.0517 0.3382 0.9946
4.750 0.7891 0.00998 0.00389 -0.0532 0.3175 0.9983
5.000 0.8155 0.01027 0.00407 -0.0530 0.2977 1.0000
5.250 0.8361 0.01053 0.00425 -0.0517 0.2790 1.0000
5.500 0.8568 0.01082 0.00445 -0.0503 0.2603 1.0000
5.750 0.8774 0.01111 0.00467 -0.0490 0.2423 1.0000
6.000 0.8980 0.01143 0.00490 -0.0476 0.2246 1.0000
6.250 0.9188 0.01177 0.00516 -0.0464 0.2070 1.0000
6.500 0.9397 0.01214 0.00543 -0.0451 0.1893 1.0000
6.750 0.9605 0.01253 0.00573 -0.0439 0.1720 1.0000
7.000 0.9815 0.01293 0.00605 -0.0427 0.1562 1.0000
7.250 1.0026 0.01333 0.00638 -0.0416 0.1416 1.0000
7.500 1.0237 0.01375 0.00673 -0.0405 0.1285 1.0000
7.750 1.0449 0.01415 0.00708 -0.0395 0.1170 1.0000
8.000 1.0660 0.01456 0.00745 -0.0384 0.1069 1.0000
8.250 1.0867 0.01499 0.00784 -0.0373 0.0977 1.0000
8.500 1.1069 0.01544 0.00825 -0.0361 0.0895 1.0000
8.750 1.1268 0.01590 0.00868 -0.0349 0.0821 1.0000
9.000 1.1467 0.01633 0.00911 -0.0337 0.0759 1.0000
9.250 1.1655 0.01682 0.00957 -0.0323 0.0703 1.0000
9.500 1.1833 0.01729 0.01004 -0.0308 0.0654 1.0000
9.750 1.1999 0.01778 0.01053 -0.0290 0.0613 1.0000
10.000 1.2162 0.01830 0.01106 -0.0273 0.0572 1.0000
10.250 1.2324 0.01886 0.01162 -0.0256 0.0539 1.0000
10.500 1.2485 0.01943 0.01221 -0.0240 0.0508 1.0000
10.750 1.2634 0.02008 0.01287 -0.0223 0.0481 1.0000
11.000 1.2791 0.02070 0.01352 -0.0208 0.0457 1.0000
11.250 1.2934 0.02142 0.01427 -0.0192 0.0434 1.0000
11.500 1.3074 0.02218 0.01506 -0.0177 0.0415 1.0000
11.750 1.3214 0.02295 0.01587 -0.0162 0.0396 1.0000
12.000 1.3340 0.02385 0.01679 -0.0147 0.0379 1.0000
12.250 1.3459 0.02481 0.01780 -0.0132 0.0365 1.0000
12.500 1.3585 0.02577 0.01882 -0.0119 0.0352 1.0000
12.750 1.3697 0.02684 0.01994 -0.0106 0.0339 1.0000
13.000 1.3794 0.02808 0.02122 -0.0093 0.0326 1.0000
13.250 1.3889 0.02938 0.02258 -0.0082 0.0316 1.0000
13.500 1.3986 0.03071 0.02398 -0.0071 0.0306 1.0000
13.750 1.4071 0.03219 0.02552 -0.0062 0.0296 1.0000
14.000 1.4141 0.03385 0.02724 -0.0053 0.0287 1.0000
14.250 1.4190 0.03576 0.02921 -0.0045 0.0279 1.0000
14.500 1.4251 0.03764 0.03117 -0.0039 0.0273 1.0000
14.750 1.4305 0.03965 0.03327 -0.0034 0.0266 1.0000
15.000 1.4346 0.04184 0.03554 -0.0031 0.0259 1.0000
15.250 1.4373 0.04424 0.03803 -0.0028 0.0253 1.0000
15.500 1.4386 0.04689 0.04075 -0.0028 0.0248 1.0000
15.750 1.4380 0.04983 0.04377 -0.0029 0.0243 1.0000
16.000 1.4356 0.05307 0.04709 -0.0032 0.0239 1.0000
16.250 1.4355 0.05613 0.05026 -0.0036 0.0234 1.0000
16.500 1.4340 0.05943 0.05367 -0.0042 0.0230 1.0000
16.750 1.4315 0.06292 0.05726 -0.0049 0.0226 1.0000
17.000 1.4277 0.06665 0.06109 -0.0057 0.0221 1.0000
17.250 1.4224 0.07065 0.06518 -0.0067 0.0218 1.0000
17.500 1.4159 0.07491 0.06954 -0.0079 0.0214 1.0000
17.750 1.4079 0.07942 0.07414 -0.0093 0.0211 1.0000
18.000 1.3984 0.08422 0.07904 -0.0109 0.0209 1.0000
18.250 1.3876 0.08932 0.08423 -0.0126 0.0206 1.0000
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