N-10 (n10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-10 (n10-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.37 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n10-il-1000000-n5.txt Download as CSV file: xf-n10-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-10
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
------ -------- --------- --------- -------- -------- --------
-16.750 -1.1057 0.03592 0.03314 -0.0942 0.9999 0.0078
-16.500 -1.1200 0.03297 0.03001 -0.0924 0.9999 0.0078
-16.250 -1.1222 0.03077 0.02766 -0.0906 0.9999 0.0080
-16.000 -1.1189 0.02899 0.02574 -0.0886 0.9999 0.0081
-15.750 -1.1120 0.02748 0.02410 -0.0866 0.9999 0.0083
-15.500 -1.1024 0.02617 0.02265 -0.0847 0.9999 0.0085
-15.250 -1.0925 0.02480 0.02116 -0.0827 0.9999 0.0088
-15.000 -1.0737 0.02340 0.01962 -0.0824 0.9992 0.0092
-14.750 -1.0484 0.02216 0.01828 -0.0830 0.9979 0.0097
-14.500 -1.0219 0.02109 0.01709 -0.0837 0.9965 0.0102
-14.250 -0.9939 0.02012 0.01602 -0.0844 0.9952 0.0106
-14.000 -0.9650 0.01926 0.01505 -0.0852 0.9942 0.0111
-13.750 -0.9388 0.01846 0.01417 -0.0854 0.9922 0.0118
-13.500 -0.9109 0.01777 0.01342 -0.0857 0.9902 0.0125
-13.250 -0.8817 0.01715 0.01275 -0.0863 0.9884 0.0133
-13.000 -0.8514 0.01656 0.01207 -0.0870 0.9868 0.0141
-12.750 -0.8203 0.01605 0.01151 -0.0879 0.9855 0.0149
-12.500 -0.7900 0.01571 0.01117 -0.0884 0.9838 0.0158
-12.250 -0.7623 0.01538 0.01081 -0.0884 0.9801 0.0167
-12.000 -0.7325 0.01500 0.01037 -0.0888 0.9768 0.0175
-11.750 -0.7016 0.01459 0.00989 -0.0894 0.9741 0.0180
-11.500 -0.6752 0.01418 0.00942 -0.0891 0.9682 0.0185
-11.250 -0.6447 0.01385 0.00907 -0.0896 0.9629 0.0192
-11.000 -0.6160 0.01363 0.00884 -0.0897 0.9549 0.0198
-10.750 -0.5862 0.01341 0.00859 -0.0899 0.9474 0.0205
-10.500 -0.5580 0.01315 0.00827 -0.0899 0.9371 0.0211
-10.250 -0.5301 0.01286 0.00791 -0.0898 0.9248 0.0217
-10.000 -0.5026 0.01263 0.00759 -0.0895 0.9102 0.0222
-9.750 -0.4755 0.01244 0.00729 -0.0891 0.8949 0.0226
-9.500 -0.4487 0.01226 0.00701 -0.0887 0.8788 0.0229
-9.250 -0.4231 0.01187 0.00649 -0.0882 0.8619 0.0235
-9.000 -0.3972 0.01151 0.00603 -0.0877 0.8468 0.0242
-8.750 -0.3704 0.01128 0.00574 -0.0874 0.8350 0.0248
-8.500 -0.3432 0.01110 0.00548 -0.0871 0.8250 0.0253
-8.250 -0.3160 0.01088 0.00519 -0.0868 0.8150 0.0258
-8.000 -0.2885 0.01067 0.00493 -0.0866 0.8070 0.0264
-7.750 -0.2611 0.01045 0.00463 -0.0864 0.7990 0.0269
-7.500 -0.2335 0.01021 0.00433 -0.0862 0.7909 0.0273
-7.250 -0.2060 0.01001 0.00406 -0.0860 0.7817 0.0277
-7.000 -0.1783 0.00982 0.00381 -0.0858 0.7712 0.0281
-6.750 -0.1506 0.00966 0.00359 -0.0857 0.7603 0.0285
-6.500 -0.1229 0.00953 0.00338 -0.0855 0.7481 0.0287
-6.250 -0.0952 0.00939 0.00317 -0.0853 0.7344 0.0289
-6.000 -0.0678 0.00916 0.00286 -0.0851 0.7180 0.0295
-5.750 -0.0405 0.00901 0.00260 -0.0848 0.6971 0.0302
-5.500 -0.0134 0.00892 0.00240 -0.0846 0.6746 0.0310
-5.250 0.0140 0.00885 0.00225 -0.0844 0.6554 0.0317
-5.000 0.0416 0.00879 0.00211 -0.0842 0.6403 0.0326
-4.500 0.0975 0.00867 0.00188 -0.0840 0.6170 0.0345
-4.250 0.1256 0.00862 0.00179 -0.0840 0.6065 0.0355
-4.000 0.1537 0.00858 0.00170 -0.0839 0.5969 0.0371
-3.750 0.1820 0.00849 0.00161 -0.0840 0.5889 0.0411
-3.500 0.2100 0.00844 0.00154 -0.0839 0.5798 0.0458
-3.250 0.2382 0.00835 0.00148 -0.0840 0.5692 0.0591
-3.000 0.2661 0.00828 0.00144 -0.0839 0.5563 0.0777
-2.750 0.2939 0.00825 0.00140 -0.0839 0.5395 0.0918
-2.500 0.3214 0.00828 0.00137 -0.0838 0.5154 0.1040
-2.250 0.3478 0.00838 0.00136 -0.0836 0.4739 0.1231
-2.000 0.3733 0.00847 0.00143 -0.0833 0.4292 0.1839
-1.750 0.3995 0.00864 0.00151 -0.0831 0.3951 0.2059
-1.500 0.4266 0.00873 0.00156 -0.0830 0.3731 0.2275
-1.250 0.4541 0.00877 0.00160 -0.0830 0.3606 0.2458
-0.750 0.5088 0.00857 0.00170 -0.0831 0.3430 0.3797
-0.500 0.5359 0.00848 0.00178 -0.0831 0.3344 0.4569
-0.250 0.5632 0.00839 0.00185 -0.0832 0.3271 0.5300
0.000 0.5899 0.00821 0.00193 -0.0831 0.3205 0.6342
0.250 0.6156 0.00796 0.00203 -0.0828 0.3161 0.7626
0.500 0.6393 0.00775 0.00213 -0.0818 0.3123 0.8680
0.750 0.6664 0.00768 0.00223 -0.0814 0.3075 0.9737
1.000 0.7039 0.00780 0.00231 -0.0836 0.3018 1.0001
1.250 0.7311 0.00789 0.00238 -0.0836 0.2992 1.0001
1.500 0.7583 0.00799 0.00246 -0.0835 0.2959 1.0001
1.750 0.7853 0.00811 0.00255 -0.0835 0.2913 1.0001
2.000 0.8121 0.00824 0.00266 -0.0834 0.2871 1.0001
2.250 0.8394 0.00834 0.00276 -0.0834 0.2843 1.0001
2.500 0.8667 0.00845 0.00286 -0.0834 0.2810 1.0001
2.750 0.8937 0.00857 0.00297 -0.0834 0.2767 1.0001
3.000 0.9203 0.00873 0.00310 -0.0833 0.2713 1.0001
3.250 0.9475 0.00884 0.00322 -0.0833 0.2672 1.0001
3.500 0.9743 0.00899 0.00335 -0.0833 0.2612 1.0001
3.750 1.0007 0.00915 0.00349 -0.0832 0.2541 1.0001
4.000 1.0264 0.00939 0.00366 -0.0831 0.2378 1.0001
4.250 1.0480 0.00997 0.00397 -0.0823 0.1891 1.0001
4.500 1.0682 0.01068 0.00444 -0.0813 0.1487 1.0001
4.750 1.0919 0.01108 0.00476 -0.0808 0.1339 1.0001
5.000 1.1166 0.01138 0.00503 -0.0805 0.1254 1.0001
5.250 1.1407 0.01172 0.00532 -0.0801 0.1166 1.0001
5.500 1.1656 0.01198 0.00558 -0.0799 0.1110 1.0001
5.750 1.1899 0.01228 0.00586 -0.0795 0.1057 1.0001
6.000 1.2142 0.01257 0.00614 -0.0792 0.0999 1.0001
6.250 1.2372 0.01296 0.00647 -0.0787 0.0894 1.0001
6.500 1.2573 0.01359 0.00693 -0.0778 0.0647 1.0001
6.750 1.2735 0.01450 0.00768 -0.0762 0.0370 1.0001
7.000 1.2890 0.01544 0.00849 -0.0745 0.0155 1.0001
7.250 1.3103 0.01588 0.00894 -0.0737 0.0134 1.0001
7.500 1.3306 0.01636 0.00944 -0.0728 0.0118 1.0001
7.750 1.3511 0.01680 0.00991 -0.0720 0.0108 1.0001
8.000 1.3711 0.01724 0.01039 -0.0710 0.0102 1.0001
8.250 1.3898 0.01772 0.01089 -0.0699 0.0096 1.0001
8.500 1.4060 0.01824 0.01144 -0.0683 0.0090 1.0001
8.750 1.4207 0.01884 0.01208 -0.0664 0.0084 1.0001
9.000 1.4362 0.01940 0.01269 -0.0648 0.0081 1.0001
9.250 1.4516 0.01998 0.01332 -0.0633 0.0078 1.0001
9.500 1.4665 0.02060 0.01398 -0.0618 0.0074 1.0001
9.750 1.4807 0.02128 0.01470 -0.0602 0.0071 1.0001
10.000 1.4939 0.02203 0.01550 -0.0586 0.0068 1.0001
10.250 1.5059 0.02288 0.01640 -0.0570 0.0065 1.0001
10.500 1.5162 0.02388 0.01745 -0.0553 0.0062 1.0001
10.750 1.5259 0.02496 0.01860 -0.0536 0.0060 1.0001
11.000 1.5367 0.02600 0.01971 -0.0522 0.0059 1.0001
11.250 1.5466 0.02715 0.02093 -0.0509 0.0057 1.0001
11.500 1.5556 0.02843 0.02227 -0.0496 0.0056 1.0001
11.750 1.5638 0.02981 0.02373 -0.0484 0.0054 1.0001
12.000 1.5710 0.03134 0.02533 -0.0473 0.0053 1.0001
12.250 1.5773 0.03301 0.02707 -0.0463 0.0052 1.0001
12.500 1.5826 0.03482 0.02897 -0.0454 0.0050 1.0001
12.750 1.5869 0.03680 0.03102 -0.0446 0.0049 1.0001
13.000 1.5898 0.03897 0.03328 -0.0439 0.0048 1.0001
13.250 1.5915 0.04135 0.03574 -0.0434 0.0047 1.0001
13.500 1.5916 0.04402 0.03849 -0.0430 0.0046 1.0001
13.750 1.5892 0.04705 0.04161 -0.0428 0.0045 1.0001
14.000 1.5845 0.05052 0.04519 -0.0428 0.0044 1.0001
14.250 1.5765 0.05455 0.04933 -0.0431 0.0043 1.0001
14.500 1.5716 0.05828 0.05317 -0.0435 0.0042 1.0001
14.750 1.5657 0.06225 0.05724 -0.0441 0.0042 1.0001
15.000 1.5587 0.06650 0.06160 -0.0450 0.0042 1.0001
15.250 1.5486 0.07132 0.06654 -0.0461 0.0041 1.0001
15.500 1.5378 0.07637 0.07171 -0.0474 0.0041 1.0001
15.750 1.5258 0.08175 0.07721 -0.0489 0.0041 1.0001
16.000 1.5119 0.08756 0.08315 -0.0507 0.0040 1.0001
16.250 1.4975 0.09351 0.08922 -0.0526 0.0040 1.0001
16.500 1.4829 0.09952 0.09535 -0.0546 0.0040 1.0001
16.750 1.4670 0.10583 0.10177 -0.0568 0.0040 1.0001
17.000 1.4518 0.11205 0.10810 -0.0591 0.0040 1.0001
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Polar data table (+)
Polar graphs
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