NACA 2415 (n2415-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2415 (n2415-il) Reynolds number: 500,000 Max Cl/Cd: 87.12 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n2415-il-500000.txt Download as CSV file: xf-n2415-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.9960 0.10314 0.09953 -0.0403 1.0000 0.0296
-18.250 -1.0198 0.09513 0.09136 -0.0450 1.0000 0.0298
-18.000 -1.0400 0.08796 0.08405 -0.0493 1.0000 0.0300
-17.750 -1.0572 0.08146 0.07740 -0.0531 1.0000 0.0301
-17.500 -1.0727 0.07541 0.07121 -0.0567 1.0000 0.0303
-17.250 -1.0861 0.06985 0.06551 -0.0599 1.0000 0.0306
-17.000 -1.0977 0.06467 0.06019 -0.0629 1.0000 0.0308
-16.750 -1.1075 0.05986 0.05523 -0.0657 1.0000 0.0310
-16.500 -1.1153 0.05539 0.05061 -0.0683 1.0000 0.0313
-16.250 -1.1210 0.05130 0.04636 -0.0707 1.0000 0.0315
-16.000 -1.1256 0.04784 0.04285 -0.0717 1.0000 0.0319
-15.750 -1.1264 0.04476 0.03972 -0.0729 1.0000 0.0323
-15.500 -1.1250 0.04200 0.03689 -0.0740 1.0000 0.0327
-15.250 -1.1225 0.03944 0.03427 -0.0749 1.0000 0.0331
-15.000 -1.1194 0.03710 0.03185 -0.0755 1.0000 0.0336
-14.750 -1.1157 0.03496 0.02961 -0.0757 1.0000 0.0341
-14.500 -1.1113 0.03304 0.02760 -0.0755 1.0000 0.0346
-14.250 -1.1063 0.03135 0.02579 -0.0750 1.0000 0.0351
-14.000 -1.1003 0.02992 0.02422 -0.0740 1.0000 0.0356
-13.750 -1.0971 0.02839 0.02262 -0.0724 1.0000 0.0361
-13.500 -1.0946 0.02707 0.02128 -0.0702 1.0000 0.0367
-13.250 -1.0915 0.02613 0.02031 -0.0674 1.0000 0.0373
-13.000 -1.0916 0.02542 0.01956 -0.0636 1.0000 0.0378
-12.750 -1.0925 0.02483 0.01893 -0.0592 1.0000 0.0384
-12.500 -1.0880 0.02423 0.01827 -0.0557 1.0000 0.0392
-12.250 -1.0823 0.02368 0.01765 -0.0523 1.0000 0.0400
-12.000 -1.0748 0.02322 0.01708 -0.0490 1.0000 0.0406
-11.750 -1.0730 0.02230 0.01617 -0.0451 1.0000 0.0415
-11.500 -1.0651 0.02173 0.01559 -0.0420 1.0000 0.0423
-11.250 -1.0550 0.02124 0.01507 -0.0392 1.0000 0.0433
-11.000 -1.0435 0.02077 0.01455 -0.0366 1.0000 0.0443
-10.750 -1.0223 0.02030 0.01399 -0.0358 0.9993 0.0455
-10.500 -0.9923 0.01941 0.01310 -0.0371 0.9970 0.0472
-10.250 -0.9591 0.01888 0.01256 -0.0388 0.9949 0.0490
-10.000 -0.9243 0.01844 0.01205 -0.0406 0.9933 0.0511
-9.750 -0.8948 0.01771 0.01131 -0.0415 0.9902 0.0531
-9.500 -0.8621 0.01721 0.01081 -0.0429 0.9874 0.0553
-9.250 -0.8271 0.01682 0.01036 -0.0446 0.9851 0.0577
-9.000 -0.7929 0.01616 0.00973 -0.0464 0.9832 0.0608
-8.750 -0.7558 0.01578 0.00932 -0.0485 0.9818 0.0640
-8.500 -0.7279 0.01525 0.00879 -0.0488 0.9768 0.0671
-8.250 -0.6935 0.01485 0.00839 -0.0504 0.9739 0.0710
-8.000 -0.6575 0.01436 0.00790 -0.0523 0.9718 0.0754
-7.750 -0.6194 0.01396 0.00751 -0.0546 0.9703 0.0804
-7.500 -0.5812 0.01347 0.00705 -0.0569 0.9689 0.0862
-7.250 -0.5533 0.01318 0.00673 -0.0569 0.9625 0.0913
-7.000 -0.5203 0.01271 0.00633 -0.0581 0.9589 0.0984
-6.750 -0.4862 0.01232 0.00595 -0.0594 0.9560 0.1060
-6.500 -0.4581 0.01203 0.00568 -0.0594 0.9502 0.1135
-6.250 -0.4299 0.01166 0.00536 -0.0594 0.9442 0.1227
-6.000 -0.3994 0.01132 0.00505 -0.0599 0.9397 0.1327
-5.750 -0.3741 0.01107 0.00482 -0.0592 0.9317 0.1426
-5.500 -0.3462 0.01079 0.00457 -0.0591 0.9252 0.1543
-5.250 -0.3198 0.01051 0.00434 -0.0587 0.9176 0.1673
-5.000 -0.2933 0.01025 0.00412 -0.0583 0.9093 0.1810
-4.750 -0.2664 0.01001 0.00392 -0.0579 0.9014 0.1959
-4.500 -0.2399 0.00978 0.00373 -0.0575 0.8921 0.2114
-4.250 -0.2129 0.00958 0.00356 -0.0572 0.8830 0.2280
-4.000 -0.1861 0.00938 0.00339 -0.0568 0.8731 0.2455
-3.750 -0.1593 0.00919 0.00325 -0.0564 0.8627 0.2639
-3.500 -0.1320 0.00902 0.00310 -0.0561 0.8526 0.2834
-3.250 -0.1053 0.00886 0.00298 -0.0558 0.8408 0.3038
-3.000 -0.0782 0.00872 0.00286 -0.0555 0.8296 0.3254
-2.750 -0.0512 0.00858 0.00275 -0.0551 0.8174 0.3476
-2.500 -0.0245 0.00842 0.00265 -0.0547 0.8047 0.3718
-2.250 0.0023 0.00829 0.00256 -0.0544 0.7921 0.3987
-1.750 0.0552 0.00800 0.00242 -0.0536 0.7650 0.4638
-1.500 0.0815 0.00787 0.00237 -0.0531 0.7510 0.5016
-1.250 0.1078 0.00776 0.00234 -0.0526 0.7371 0.5393
-1.000 0.1339 0.00768 0.00231 -0.0521 0.7228 0.5766
-0.750 0.1601 0.00761 0.00230 -0.0516 0.7079 0.6127
-0.500 0.1863 0.00754 0.00231 -0.0510 0.6931 0.6471
-0.250 0.2124 0.00749 0.00232 -0.0505 0.6786 0.6802
0.000 0.2384 0.00747 0.00234 -0.0499 0.6642 0.7126
0.250 0.2642 0.00747 0.00237 -0.0492 0.6499 0.7449
0.500 0.2901 0.00745 0.00242 -0.0485 0.6354 0.7761
0.750 0.3160 0.00747 0.00248 -0.0478 0.6214 0.8062
1.000 0.3415 0.00750 0.00256 -0.0470 0.6081 0.8350
1.500 0.3927 0.00764 0.00273 -0.0454 0.5816 0.8868
1.750 0.4188 0.00775 0.00283 -0.0447 0.5689 0.9091
2.000 0.4457 0.00789 0.00293 -0.0441 0.5565 0.9283
2.250 0.4748 0.00804 0.00304 -0.0441 0.5436 0.9443
2.500 0.5062 0.00819 0.00316 -0.0446 0.5313 0.9574
2.750 0.5385 0.00837 0.00328 -0.0454 0.5192 0.9687
3.000 0.5769 0.00855 0.00340 -0.0476 0.5061 0.9751
3.250 0.6145 0.00872 0.00353 -0.0496 0.4932 0.9818
3.500 0.6561 0.00889 0.00365 -0.0525 0.4796 0.9855
3.750 0.6955 0.00909 0.00377 -0.0550 0.4656 0.9905
4.000 0.7362 0.00927 0.00389 -0.0578 0.4511 0.9948
4.250 0.7805 0.00943 0.00401 -0.0614 0.4360 0.9991
4.500 0.8067 0.00956 0.00410 -0.0612 0.4228 1.0000
4.750 0.8269 0.00970 0.00419 -0.0597 0.4102 1.0000
5.250 0.8671 0.01002 0.00442 -0.0568 0.3825 1.0000
5.500 0.8872 0.01020 0.00455 -0.0552 0.3678 1.0000
5.750 0.9069 0.01041 0.00470 -0.0537 0.3522 1.0000
6.000 0.9266 0.01065 0.00488 -0.0521 0.3365 1.0000
6.250 0.9461 0.01090 0.00506 -0.0505 0.3204 1.0000
6.500 0.9656 0.01118 0.00527 -0.0489 0.3040 1.0000
6.750 0.9849 0.01148 0.00550 -0.0473 0.2872 1.0000
7.000 1.0043 0.01180 0.00575 -0.0457 0.2701 1.0000
7.250 1.0238 0.01215 0.00603 -0.0442 0.2526 1.0000
7.500 1.0434 0.01253 0.00633 -0.0428 0.2350 1.0000
7.750 1.0628 0.01294 0.00665 -0.0413 0.2176 1.0000
8.000 1.0821 0.01337 0.00700 -0.0399 0.2009 1.0000
8.250 1.1011 0.01383 0.00738 -0.0384 0.1848 1.0000
8.500 1.1198 0.01430 0.00778 -0.0369 0.1697 1.0000
8.750 1.1381 0.01479 0.00820 -0.0354 0.1559 1.0000
9.000 1.1559 0.01529 0.00865 -0.0338 0.1432 1.0000
9.250 1.1721 0.01580 0.00911 -0.0320 0.1318 1.0000
9.500 1.1870 0.01635 0.00961 -0.0299 0.1216 1.0000
9.750 1.2011 0.01696 0.01017 -0.0278 0.1123 1.0000
10.000 1.2168 0.01752 0.01072 -0.0260 0.1042 1.0000
10.250 1.2317 0.01814 0.01133 -0.0242 0.0971 1.0000
10.500 1.2442 0.01891 0.01205 -0.0222 0.0904 1.0000
10.750 1.2599 0.01952 0.01269 -0.0206 0.0849 1.0000
11.000 1.2721 0.02036 0.01351 -0.0187 0.0799 1.0000
11.250 1.2864 0.02109 0.01427 -0.0171 0.0753 1.0000
11.500 1.2968 0.02209 0.01525 -0.0153 0.0713 1.0000
11.750 1.3107 0.02289 0.01610 -0.0138 0.0678 1.0000
12.000 1.3196 0.02405 0.01725 -0.0121 0.0645 1.0000
12.250 1.3318 0.02503 0.01830 -0.0107 0.0618 1.0000
12.500 1.3424 0.02616 0.01945 -0.0093 0.0591 1.0000
12.750 1.3471 0.02776 0.02106 -0.0076 0.0568 1.0000
13.000 1.3591 0.02889 0.02227 -0.0066 0.0548 1.0000
13.250 1.3681 0.03027 0.02371 -0.0055 0.0528 1.0000
13.500 1.3726 0.03209 0.02554 -0.0044 0.0510 1.0000
13.750 1.3779 0.03392 0.02744 -0.0034 0.0494 1.0000
14.000 1.3857 0.03557 0.02917 -0.0027 0.0479 1.0000
14.250 1.3913 0.03749 0.03116 -0.0020 0.0465 1.0000
14.500 1.3929 0.03986 0.03356 -0.0015 0.0453 1.0000
14.750 1.3907 0.04265 0.03640 -0.0009 0.0442 1.0000
15.000 1.3964 0.04477 0.03863 -0.0007 0.0431 1.0000
15.250 1.3997 0.04719 0.04113 -0.0006 0.0421 1.0000
15.500 1.4017 0.04982 0.04383 -0.0006 0.0410 1.0000
15.750 1.4004 0.05286 0.04693 -0.0008 0.0402 1.0000
16.000 1.3942 0.05650 0.05061 -0.0010 0.0393 1.0000
16.250 1.3946 0.05951 0.05373 -0.0014 0.0386 1.0000
16.500 1.3949 0.06258 0.05691 -0.0018 0.0378 1.0000
16.750 1.3938 0.06587 0.06029 -0.0024 0.0370 1.0000
17.000 1.3917 0.06933 0.06382 -0.0032 0.0363 1.0000
17.250 1.3886 0.07298 0.06754 -0.0040 0.0357 1.0000
17.500 1.3834 0.07688 0.07150 -0.0049 0.0351 1.0000
17.750 1.3760 0.08094 0.07558 -0.0057 0.0344 1.0000
18.000 1.3736 0.08467 0.07943 -0.0068 0.0340 1.0000
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