NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2.5411 (naca2411-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.68 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2411-il-1000000-n5.txt Download as CSV file: xf-naca2411-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2.5411
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.9170 0.08561 0.08307 -0.0473 1.0000 0.0110
-16.000 -0.9880 0.07041 0.06771 -0.0565 1.0000 0.0109
-15.750 -1.0800 0.05077 0.04779 -0.0699 1.0000 0.0106
-15.500 -1.1173 0.03920 0.03594 -0.0805 1.0000 0.0106
-15.250 -1.1345 0.03406 0.03062 -0.0842 1.0000 0.0106
-15.000 -1.1412 0.03148 0.02792 -0.0841 1.0000 0.0107
-14.750 -1.1497 0.02950 0.02582 -0.0821 1.0000 0.0107
-14.500 -1.1565 0.02820 0.02442 -0.0785 1.0000 0.0108
-14.250 -1.1603 0.02719 0.02333 -0.0745 1.0000 0.0109
-14.000 -1.1574 0.02610 0.02214 -0.0715 1.0000 0.0110
-13.750 -1.1520 0.02514 0.02109 -0.0687 1.0000 0.0111
-13.500 -1.1448 0.02428 0.02014 -0.0660 1.0000 0.0112
-13.250 -1.1365 0.02347 0.01923 -0.0633 1.0000 0.0113
-13.000 -1.1128 0.02255 0.01821 -0.0637 0.9990 0.0115
-12.750 -1.0871 0.02170 0.01726 -0.0643 0.9975 0.0116
-12.500 -1.0633 0.02052 0.01597 -0.0649 0.9956 0.0119
-12.250 -1.0368 0.01965 0.01504 -0.0656 0.9941 0.0122
-12.000 -1.0126 0.01891 0.01422 -0.0656 0.9921 0.0125
-11.750 -0.9867 0.01826 0.01352 -0.0659 0.9900 0.0127
-11.500 -0.9596 0.01764 0.01282 -0.0664 0.9881 0.0130
-11.250 -0.9316 0.01702 0.01213 -0.0670 0.9864 0.0132
-11.000 -0.9027 0.01642 0.01146 -0.0677 0.9850 0.0135
-10.750 -0.8730 0.01587 0.01084 -0.0685 0.9838 0.0138
-10.500 -0.8476 0.01535 0.01026 -0.0684 0.9810 0.0140
-10.250 -0.8209 0.01488 0.00972 -0.0685 0.9781 0.0143
-10.000 -0.7922 0.01442 0.00920 -0.0689 0.9759 0.0145
-9.750 -0.7633 0.01381 0.00854 -0.0696 0.9740 0.0151
-9.500 -0.7326 0.01332 0.00801 -0.0705 0.9725 0.0156
-9.250 -0.7006 0.01288 0.00754 -0.0716 0.9712 0.0160
-9.000 -0.6748 0.01251 0.00712 -0.0713 0.9668 0.0165
-8.750 -0.6465 0.01213 0.00671 -0.0716 0.9630 0.0169
-8.500 -0.6156 0.01178 0.00630 -0.0723 0.9600 0.0174
-8.250 -0.5833 0.01144 0.00592 -0.0734 0.9573 0.0178
-8.000 -0.5572 0.01108 0.00552 -0.0731 0.9516 0.0185
-7.750 -0.5281 0.01073 0.00516 -0.0735 0.9463 0.0195
-7.500 -0.4976 0.01044 0.00484 -0.0741 0.9409 0.0205
-7.250 -0.4703 0.01019 0.00455 -0.0740 0.9321 0.0214
-7.000 -0.4419 0.00992 0.00424 -0.0741 0.9235 0.0225
-6.750 -0.4148 0.00967 0.00396 -0.0739 0.9144 0.0242
-6.500 -0.3878 0.00946 0.00372 -0.0737 0.9062 0.0258
-6.250 -0.3610 0.00925 0.00347 -0.0734 0.8974 0.0277
-6.000 -0.3346 0.00905 0.00326 -0.0730 0.8883 0.0301
-5.750 -0.3080 0.00889 0.00305 -0.0727 0.8789 0.0325
-5.500 -0.2819 0.00870 0.00285 -0.0723 0.8684 0.0361
-5.250 -0.2556 0.00856 0.00268 -0.0719 0.8579 0.0394
-5.000 -0.2296 0.00841 0.00250 -0.0714 0.8470 0.0434
-4.750 -0.2035 0.00829 0.00234 -0.0709 0.8350 0.0470
-4.500 -0.1774 0.00815 0.00220 -0.0704 0.8231 0.0519
-4.250 -0.1514 0.00805 0.00206 -0.0700 0.8108 0.0570
-4.000 -0.1256 0.00794 0.00193 -0.0694 0.7981 0.0636
-3.750 -0.0999 0.00783 0.00181 -0.0689 0.7850 0.0718
-3.500 -0.0742 0.00773 0.00169 -0.0683 0.7711 0.0814
-3.250 -0.0484 0.00764 0.00159 -0.0678 0.7569 0.0921
-3.000 -0.0226 0.00756 0.00150 -0.0673 0.7426 0.1034
-2.750 0.0032 0.00749 0.00142 -0.0668 0.7278 0.1156
-2.500 0.0289 0.00742 0.00134 -0.0662 0.7128 0.1300
-2.000 0.0802 0.00728 0.00122 -0.0651 0.6824 0.1646
-1.750 0.1059 0.00723 0.00117 -0.0646 0.6672 0.1836
-1.500 0.1315 0.00718 0.00114 -0.0641 0.6511 0.2043
-1.000 0.1829 0.00710 0.00108 -0.0630 0.6210 0.2490
-0.750 0.2085 0.00706 0.00107 -0.0625 0.6055 0.2757
-0.500 0.2342 0.00702 0.00107 -0.0620 0.5905 0.3046
-0.250 0.2597 0.00699 0.00107 -0.0615 0.5757 0.3352
0.000 0.2852 0.00694 0.00107 -0.0609 0.5613 0.3698
0.250 0.3102 0.00686 0.00108 -0.0603 0.5473 0.4160
0.500 0.3349 0.00675 0.00111 -0.0597 0.5340 0.4746
0.750 0.3594 0.00664 0.00114 -0.0590 0.5209 0.5391
1.000 0.3839 0.00656 0.00118 -0.0582 0.5083 0.5967
1.250 0.4083 0.00649 0.00123 -0.0574 0.4964 0.6496
1.500 0.4320 0.00642 0.00129 -0.0565 0.4840 0.7050
1.750 0.4551 0.00634 0.00135 -0.0553 0.4719 0.7641
2.000 0.4781 0.00627 0.00142 -0.0542 0.4604 0.8195
2.250 0.5017 0.00622 0.00151 -0.0530 0.4489 0.8781
2.500 0.5328 0.00627 0.00163 -0.0536 0.4360 0.9270
2.750 0.5744 0.00643 0.00176 -0.0566 0.4180 0.9542
3.000 0.6150 0.00662 0.00187 -0.0594 0.3972 0.9680
3.250 0.6537 0.00684 0.00200 -0.0619 0.3746 0.9768
3.500 0.6869 0.00712 0.00214 -0.0631 0.3457 0.9859
3.750 0.7208 0.00744 0.00231 -0.0646 0.3116 0.9929
4.000 0.7563 0.00775 0.00248 -0.0665 0.2828 0.9975
4.250 0.7902 0.00809 0.00267 -0.0680 0.2508 1.0000
4.500 0.8097 0.00841 0.00286 -0.0664 0.2230 1.0000
4.750 0.8297 0.00872 0.00305 -0.0648 0.1983 1.0000
5.000 0.8491 0.00907 0.00327 -0.0632 0.1716 1.0000
5.250 0.8691 0.00940 0.00350 -0.0616 0.1502 1.0000
5.500 0.8891 0.00973 0.00373 -0.0601 0.1292 1.0000
5.750 0.9079 0.01016 0.00401 -0.0584 0.1036 1.0000
6.000 0.9278 0.01051 0.00428 -0.0568 0.0870 1.0000
6.250 0.9483 0.01084 0.00454 -0.0554 0.0744 1.0000
6.500 0.9689 0.01115 0.00480 -0.0540 0.0641 1.0000
6.750 0.9897 0.01146 0.00507 -0.0527 0.0560 1.0000
7.000 1.0105 0.01176 0.00534 -0.0514 0.0496 1.0000
7.250 1.0311 0.01208 0.00562 -0.0500 0.0442 1.0000
7.500 1.0521 0.01236 0.00590 -0.0487 0.0403 1.0000
7.750 1.0723 0.01269 0.00621 -0.0473 0.0361 1.0000
8.000 1.0930 0.01299 0.00650 -0.0460 0.0330 1.0000
8.500 1.1329 0.01366 0.00716 -0.0432 0.0270 1.0000
8.750 1.1522 0.01402 0.00752 -0.0417 0.0248 1.0000
9.000 1.1717 0.01436 0.00787 -0.0403 0.0231 1.0000
9.250 1.1905 0.01472 0.00824 -0.0387 0.0214 1.0000
9.500 1.2082 0.01513 0.00865 -0.0370 0.0198 1.0000
9.750 1.2250 0.01549 0.00903 -0.0351 0.0188 1.0000
10.000 1.2407 0.01586 0.00943 -0.0330 0.0178 1.0000
10.250 1.2555 0.01629 0.00988 -0.0308 0.0168 1.0000
10.500 1.2699 0.01676 0.01036 -0.0286 0.0158 1.0000
10.750 1.2855 0.01719 0.01084 -0.0266 0.0152 1.0000
11.000 1.3006 0.01766 0.01134 -0.0247 0.0148 1.0000
11.250 1.3153 0.01817 0.01189 -0.0227 0.0142 1.0000
11.500 1.3292 0.01873 0.01248 -0.0207 0.0137 1.0000
11.750 1.3422 0.01936 0.01314 -0.0187 0.0132 1.0000
12.000 1.3546 0.02005 0.01388 -0.0167 0.0129 1.0000
12.250 1.3669 0.02076 0.01463 -0.0148 0.0126 1.0000
12.500 1.3795 0.02147 0.01540 -0.0130 0.0123 1.0000
12.750 1.3913 0.02225 0.01624 -0.0112 0.0121 1.0000
13.000 1.4030 0.02307 0.01712 -0.0096 0.0119 1.0000
13.250 1.4140 0.02396 0.01807 -0.0079 0.0116 1.0000
13.500 1.4238 0.02497 0.01914 -0.0063 0.0114 1.0000
13.750 1.4337 0.02603 0.02025 -0.0048 0.0111 1.0000
14.000 1.4421 0.02722 0.02150 -0.0034 0.0109 1.0000
14.250 1.4498 0.02854 0.02288 -0.0020 0.0106 1.0000
14.500 1.4563 0.03001 0.02442 -0.0008 0.0104 1.0000
14.750 1.4602 0.03177 0.02625 0.0004 0.0102 1.0000
15.000 1.4635 0.03368 0.02825 0.0014 0.0100 1.0000
15.250 1.4659 0.03575 0.03041 0.0022 0.0099 1.0000
15.500 1.4708 0.03767 0.03241 0.0028 0.0098 1.0000
15.750 1.4746 0.03978 0.03460 0.0032 0.0098 1.0000
16.000 1.4769 0.04211 0.03703 0.0034 0.0096 1.0000
16.250 1.4780 0.04466 0.03967 0.0035 0.0095 1.0000
16.500 1.4787 0.04735 0.04246 0.0034 0.0095 1.0000
16.750 1.4761 0.05052 0.04573 0.0031 0.0094 1.0000
17.000 1.4745 0.05365 0.04896 0.0026 0.0092 1.0000
17.250 1.4708 0.05715 0.05256 0.0019 0.0091 1.0000
17.500 1.4683 0.06059 0.05608 0.0011 0.0089 1.0000
17.750 1.4594 0.06495 0.06056 -0.0001 0.0090 1.0000
18.000 1.4549 0.06877 0.06447 -0.0012 0.0088 1.0000
18.250 1.4435 0.07371 0.06953 -0.0028 0.0088 1.0000
18.500 1.4333 0.07853 0.07445 -0.0044 0.0088 1.0000
18.750 1.4239 0.08331 0.07933 -0.0061 0.0086 1.0000
19.000 1.4104 0.08884 0.08497 -0.0082 0.0086 1.0000
19.250 1.3960 0.09464 0.09089 -0.0105 0.0086 1.0000
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