N-10 (n10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-10 (n10-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.73 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n10-il-1000000.txt Download as CSV file: xf-n10-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9998 0.03592 0.03338 -0.0888 0.9999 0.0139
-15.250 -1.0080 0.03333 0.03061 -0.0871 0.9999 0.0140
-15.000 -1.0050 0.03165 0.02880 -0.0853 0.9999 0.0141
-14.750 -1.0146 0.02869 0.02560 -0.0825 0.9999 0.0145
-14.500 -1.0047 0.02756 0.02441 -0.0806 0.9999 0.0148
-14.250 -0.9875 0.02715 0.02400 -0.0790 0.9999 0.0151
-14.000 -0.9689 0.02691 0.02376 -0.0775 0.9999 0.0154
-13.750 -0.9512 0.02656 0.02340 -0.0759 0.9999 0.0157
-13.500 -0.9350 0.02600 0.02277 -0.0742 0.9999 0.0161
-13.250 -0.9201 0.02522 0.02190 -0.0724 0.9999 0.0164
-13.000 -0.8946 0.02424 0.02078 -0.0728 0.9991 0.0169
-12.750 -0.8636 0.02341 0.01982 -0.0741 0.9978 0.0173
-12.500 -0.8357 0.02163 0.01780 -0.0756 0.9962 0.0179
-12.250 -0.8038 0.02083 0.01695 -0.0770 0.9949 0.0184
-12.000 -0.7691 0.02065 0.01678 -0.0785 0.9940 0.0189
-11.750 -0.7371 0.02046 0.01658 -0.0794 0.9920 0.0194
-11.500 -0.7048 0.02011 0.01616 -0.0804 0.9899 0.0200
-11.250 -0.6722 0.01956 0.01553 -0.0816 0.9879 0.0206
-11.000 -0.6390 0.01901 0.01485 -0.0829 0.9863 0.0212
-10.750 -0.6046 0.01874 0.01450 -0.0843 0.9851 0.0215
-10.500 -0.5751 0.01672 0.01230 -0.0858 0.9838 0.0226
-10.250 -0.5440 0.01644 0.01202 -0.0865 0.9808 0.0232
-10.000 -0.5121 0.01615 0.01169 -0.0874 0.9776 0.0238
-9.750 -0.4800 0.01567 0.01115 -0.0883 0.9746 0.0245
-9.500 -0.4476 0.01511 0.01051 -0.0893 0.9718 0.0252
-9.250 -0.4199 0.01470 0.01001 -0.0891 0.9647 0.0258
-9.000 -0.3887 0.01455 0.00979 -0.0896 0.9583 0.0263
-8.750 -0.3647 0.01298 0.00807 -0.0892 0.9473 0.0273
-8.500 -0.3373 0.01243 0.00748 -0.0890 0.9361 0.0279
-8.250 -0.3098 0.01205 0.00704 -0.0888 0.9230 0.0286
-8.000 -0.2826 0.01178 0.00669 -0.0885 0.9077 0.0294
-7.750 -0.2559 0.01146 0.00627 -0.0880 0.8921 0.0301
-7.500 -0.2293 0.01113 0.00584 -0.0876 0.8779 0.0307
-7.250 -0.2025 0.01083 0.00544 -0.0872 0.8659 0.0313
-7.000 -0.1753 0.01059 0.00512 -0.0869 0.8548 0.0317
-6.750 -0.1476 0.01046 0.00492 -0.0866 0.8444 0.0321
-6.500 -0.1222 0.00970 0.00404 -0.0861 0.8344 0.0332
-6.250 -0.0953 0.00936 0.00364 -0.0858 0.8242 0.0341
-6.000 -0.0678 0.00913 0.00337 -0.0856 0.8147 0.0350
-5.500 -0.0123 0.00876 0.00290 -0.0853 0.7965 0.0369
-5.250 0.0156 0.00863 0.00271 -0.0851 0.7873 0.0380
-5.000 0.0436 0.00849 0.00252 -0.0850 0.7768 0.0388
-4.750 0.0713 0.00829 0.00226 -0.0848 0.7653 0.0401
-4.500 0.0990 0.00811 0.00203 -0.0846 0.7520 0.0427
-4.250 0.1268 0.00800 0.00188 -0.0845 0.7368 0.0454
-4.000 0.1546 0.00791 0.00173 -0.0843 0.7208 0.0492
-3.750 0.1822 0.00776 0.00161 -0.0842 0.7043 0.0643
-3.500 0.2096 0.00762 0.00151 -0.0840 0.6875 0.0941
-3.250 0.2371 0.00752 0.00142 -0.0839 0.6719 0.1177
-3.000 0.2642 0.00733 0.00139 -0.0839 0.6581 0.1852
-2.750 0.2920 0.00729 0.00138 -0.0838 0.6458 0.2113
-2.500 0.3198 0.00729 0.00136 -0.0837 0.6343 0.2311
-2.250 0.3478 0.00724 0.00135 -0.0838 0.6235 0.2526
-2.000 0.3756 0.00715 0.00134 -0.0838 0.6132 0.2938
-1.750 0.4022 0.00684 0.00136 -0.0838 0.6012 0.4225
-1.500 0.4286 0.00656 0.00140 -0.0836 0.5866 0.5520
-1.250 0.4532 0.00611 0.00146 -0.0831 0.5699 0.7356
-1.000 0.4735 0.00577 0.00155 -0.0811 0.5524 0.8953
-0.750 0.5012 0.00584 0.00160 -0.0807 0.5210 0.9698
-0.500 0.5373 0.00623 0.00168 -0.0828 0.4548 0.9921
-0.250 0.5735 0.00659 0.00180 -0.0848 0.4116 1.0001
0.000 0.5979 0.00681 0.00190 -0.0842 0.3900 1.0001
0.250 0.6230 0.00699 0.00198 -0.0837 0.3745 1.0001
0.500 0.6488 0.00715 0.00206 -0.0833 0.3623 1.0001
0.750 0.6749 0.00730 0.00215 -0.0830 0.3531 1.0001
1.000 0.7013 0.00744 0.00224 -0.0828 0.3455 1.0001
1.250 0.7278 0.00758 0.00233 -0.0826 0.3390 1.0001
1.500 0.7547 0.00770 0.00242 -0.0825 0.3335 1.0001
1.750 0.7814 0.00784 0.00253 -0.0824 0.3281 1.0001
2.000 0.8083 0.00797 0.00264 -0.0823 0.3237 1.0001
2.250 0.8355 0.00808 0.00274 -0.0823 0.3195 1.0001
2.500 0.8624 0.00822 0.00285 -0.0822 0.3150 1.0001
2.750 0.8889 0.00838 0.00299 -0.0821 0.3105 1.0001
3.000 0.9162 0.00849 0.00311 -0.0821 0.3074 1.0001
3.250 0.9433 0.00860 0.00323 -0.0821 0.3036 1.0001
3.500 0.9701 0.00875 0.00336 -0.0821 0.2988 1.0001
3.750 0.9964 0.00893 0.00352 -0.0820 0.2936 1.0001
4.000 1.0237 0.00902 0.00364 -0.0820 0.2876 1.0001
4.250 1.0499 0.00921 0.00379 -0.0819 0.2798 1.0001
4.500 1.0768 0.00933 0.00392 -0.0820 0.2727 1.0001
4.750 1.1028 0.00954 0.00409 -0.0819 0.2630 1.0001
5.000 1.1284 0.00975 0.00426 -0.0817 0.2474 1.0001
5.250 1.1518 0.01016 0.00450 -0.0812 0.2136 1.0001
5.500 1.1696 0.01104 0.00505 -0.0799 0.1605 1.0001
5.750 1.1913 0.01159 0.00548 -0.0791 0.1409 1.0001
6.000 1.2146 0.01197 0.00582 -0.0786 0.1304 1.0001
6.250 1.2382 0.01233 0.00615 -0.0782 0.1224 1.0001
6.500 1.2620 0.01265 0.00646 -0.0778 0.1165 1.0001
6.750 1.2852 0.01301 0.00681 -0.0773 0.1094 1.0001
7.000 1.3082 0.01338 0.00714 -0.0768 0.1007 1.0001
7.250 1.3293 0.01387 0.00754 -0.0761 0.0850 1.0001
7.500 1.3358 0.01550 0.00875 -0.0730 0.0289 1.0001
7.750 1.3514 0.01635 0.00954 -0.0713 0.0182 1.0001
8.000 1.3690 0.01700 0.01021 -0.0700 0.0158 1.0001
8.250 1.3879 0.01751 0.01076 -0.0688 0.0150 1.0001
8.500 1.4046 0.01806 0.01137 -0.0673 0.0142 1.0001
8.750 1.4181 0.01873 0.01208 -0.0652 0.0134 1.0001
9.000 1.4283 0.01962 0.01304 -0.0627 0.0126 1.0001
9.250 1.4432 0.02024 0.01371 -0.0611 0.0122 1.0001
9.500 1.4570 0.02093 0.01446 -0.0594 0.0118 1.0001
9.750 1.4694 0.02172 0.01531 -0.0576 0.0114 1.0001
10.000 1.4808 0.02261 0.01626 -0.0558 0.0110 1.0001
10.250 1.4909 0.02360 0.01731 -0.0539 0.0106 1.0001
10.500 1.4985 0.02481 0.01859 -0.0519 0.0103 1.0001
10.750 1.5008 0.02646 0.02034 -0.0496 0.0100 1.0001
11.000 1.5000 0.02847 0.02247 -0.0473 0.0097 1.0001
11.250 1.5089 0.02981 0.02387 -0.0462 0.0096 1.0001
11.500 1.5159 0.03137 0.02552 -0.0450 0.0094 1.0001
11.750 1.5210 0.03316 0.02739 -0.0439 0.0092 1.0001
12.000 1.5247 0.03516 0.02948 -0.0429 0.0090 1.0001
12.250 1.5278 0.03730 0.03171 -0.0421 0.0088 1.0001
12.500 1.5293 0.03967 0.03417 -0.0415 0.0087 1.0001
12.750 1.5299 0.04224 0.03683 -0.0410 0.0085 1.0001
13.000 1.5298 0.04502 0.03969 -0.0407 0.0083 1.0001
13.250 1.5277 0.04813 0.04289 -0.0407 0.0082 1.0001
13.500 1.5236 0.05159 0.04645 -0.0408 0.0081 1.0001
13.750 1.5182 0.05536 0.05032 -0.0412 0.0079 1.0001
14.000 1.5096 0.05967 0.05473 -0.0418 0.0078 1.0001
14.250 1.4982 0.06448 0.05965 -0.0426 0.0077 1.0001
14.500 1.4851 0.06971 0.06500 -0.0437 0.0077 1.0001
14.750 1.4706 0.07529 0.07070 -0.0451 0.0076 1.0001
15.000 1.4548 0.08119 0.07672 -0.0467 0.0075 1.0001
15.250 1.4370 0.08749 0.08314 -0.0485 0.0075 1.0001
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