E176 (8.83%) (e176-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 100,000 Max Cl/Cd: 59.09 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e176-il-100000.txt Download as CSV file: xf-e176-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E176 (8.83%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3871 0.09535 0.09076 -0.0224 1.0000 0.0903
-8.000 -0.4002 0.09361 0.08917 -0.0278 1.0000 0.0923
-7.750 -0.4103 0.09097 0.08661 -0.0375 1.0000 0.0929
-7.500 -0.3826 0.08546 0.08110 -0.0268 1.0000 0.0967
-7.250 -0.3775 0.08257 0.07826 -0.0273 1.0000 0.1002
-7.000 -0.3783 0.07943 0.07521 -0.0324 1.0000 0.1048
-6.750 -0.3836 0.07521 0.07104 -0.0422 1.0000 0.1077
-6.500 -0.3722 0.07226 0.06820 -0.0361 1.0000 0.1105
-6.250 -0.3710 0.06997 0.06597 -0.0350 1.0000 0.1141
-6.000 -0.3858 0.06860 0.06468 -0.0333 1.0000 0.1169
-5.750 -0.4103 0.06736 0.06328 -0.0381 0.9995 0.1214
-5.500 -0.3845 0.06310 0.05918 -0.0364 0.9941 0.1252
-5.250 -0.3460 0.05780 0.05370 -0.0456 0.9846 0.1383
-5.000 -0.3101 0.05338 0.04912 -0.0520 0.9749 0.1526
-4.750 -0.2739 0.04944 0.04506 -0.0572 0.9665 0.1683
-4.500 -0.2358 0.04576 0.04118 -0.0629 0.9584 0.1949
-4.250 -0.1747 0.03249 0.02587 -0.0726 0.9499 0.0775
-4.000 -0.1323 0.02817 0.02098 -0.0759 0.9440 0.0706
-3.750 -0.0936 0.02588 0.01778 -0.0770 0.9350 0.0655
-3.500 -0.0518 0.02336 0.01486 -0.0794 0.9290 0.0651
-3.250 -0.0187 0.02161 0.01285 -0.0801 0.9194 0.0663
-3.000 0.0176 0.01997 0.01121 -0.0815 0.9123 0.0717
-2.750 0.0483 0.01894 0.01015 -0.0818 0.9028 0.0835
-2.500 0.0767 0.01790 0.00916 -0.0815 0.8934 0.1049
-2.250 0.1019 0.01553 0.00826 -0.0812 0.8861 0.3787
-2.000 0.1708 0.01347 0.00779 -0.0865 0.8835 1.0000
-1.750 0.1955 0.01362 0.00760 -0.0859 0.8731 1.0000
-1.500 0.2186 0.01383 0.00754 -0.0851 0.8625 1.0000
-1.250 0.2433 0.01402 0.00747 -0.0845 0.8536 1.0000
-1.000 0.2679 0.01421 0.00742 -0.0837 0.8447 1.0000
-0.750 0.2914 0.01449 0.00751 -0.0831 0.8352 1.0000
-0.500 0.3170 0.01466 0.00750 -0.0823 0.8281 1.0000
-0.250 0.3406 0.01498 0.00768 -0.0818 0.8185 1.0000
0.000 0.3654 0.01525 0.00780 -0.0811 0.8107 1.0000
0.250 0.3903 0.01550 0.00794 -0.0806 0.8028 1.0000
0.500 0.4148 0.01584 0.00819 -0.0801 0.7946 1.0000
0.750 0.4404 0.01608 0.00832 -0.0795 0.7876 1.0000
1.000 0.4646 0.01647 0.00867 -0.0791 0.7791 1.0000
1.250 0.4906 0.01670 0.00881 -0.0784 0.7727 1.0000
1.500 0.5147 0.01714 0.00924 -0.0781 0.7639 1.0000
1.750 0.5410 0.01736 0.00939 -0.0775 0.7579 1.0000
2.000 0.5648 0.01784 0.00991 -0.0772 0.7488 1.0000
2.250 0.5915 0.01803 0.01004 -0.0765 0.7431 1.0000
2.500 0.6149 0.01855 0.01061 -0.0762 0.7335 1.0000
2.750 0.6407 0.01883 0.01088 -0.0755 0.7266 1.0000
3.000 0.6653 0.01920 0.01131 -0.0750 0.7177 1.0000
3.250 0.6896 0.01959 0.01175 -0.0744 0.7089 1.0000
3.500 0.7161 0.01971 0.01188 -0.0736 0.7014 1.0000
3.750 0.7397 0.02014 0.01239 -0.0730 0.6910 1.0000
4.000 0.7649 0.02034 0.01269 -0.0721 0.6817 1.0000
4.250 0.7915 0.02033 0.01271 -0.0711 0.6727 1.0000
4.500 0.8155 0.02057 0.01305 -0.0702 0.6610 1.0000
4.750 0.8403 0.02070 0.01328 -0.0692 0.6495 1.0000
5.000 0.8658 0.02069 0.01335 -0.0681 0.6380 1.0000
5.250 0.8920 0.02055 0.01332 -0.0669 0.6259 1.0000
5.500 0.9179 0.02035 0.01322 -0.0656 0.6124 1.0000
5.750 0.9429 0.02016 0.01315 -0.0643 0.5968 1.0000
6.000 0.9680 0.01989 0.01300 -0.0629 0.5797 1.0000
6.250 0.9937 0.01947 0.01272 -0.0615 0.5613 1.0000
6.500 1.0182 0.01909 0.01248 -0.0599 0.5394 1.0000
6.750 1.0419 0.01865 0.01216 -0.0582 0.5121 1.0000
7.000 1.0620 0.01814 0.01168 -0.0559 0.4645 1.0000
7.250 1.0773 0.01823 0.01157 -0.0533 0.3832 1.0000
7.500 1.0840 0.01967 0.01224 -0.0504 0.2677 1.0000
7.750 1.0852 0.02208 0.01389 -0.0475 0.1630 1.0000
8.000 1.0768 0.02558 0.01649 -0.0435 0.0787 1.0000
8.250 1.0793 0.02793 0.01870 -0.0404 0.0587 1.0000
8.500 1.0843 0.03010 0.02077 -0.0377 0.0519 1.0000
8.750 1.0984 0.03188 0.02267 -0.0357 0.0474 1.0000
9.000 1.1162 0.03387 0.02465 -0.0343 0.0441 1.0000
9.250 1.1468 0.03735 0.02808 -0.0343 0.0411 1.0000
9.500 1.1680 0.03945 0.03050 -0.0332 0.0393 1.0000
9.750 1.1873 0.04193 0.03329 -0.0321 0.0373 1.0000
10.000 1.2047 0.04507 0.03678 -0.0310 0.0366 1.0000
10.250 1.2166 0.04863 0.04075 -0.0294 0.0368 1.0000
10.500 1.2216 0.05238 0.04493 -0.0275 0.0371 1.0000
10.750 1.2210 0.05627 0.04922 -0.0254 0.0377 1.0000
11.000 1.2142 0.05995 0.05324 -0.0229 0.0382 1.0000
11.250 1.2032 0.06367 0.05724 -0.0207 0.0388 1.0000
11.500 1.1892 0.06764 0.06147 -0.0191 0.0392 1.0000
11.750 1.1740 0.07184 0.06589 -0.0184 0.0397 1.0000
12.000 1.1585 0.07648 0.07073 -0.0184 0.0401 1.0000
12.250 1.1425 0.08169 0.07611 -0.0191 0.0406 1.0000
12.500 1.1375 0.08759 0.08214 -0.0197 0.0416 1.0000
12.750 1.1169 0.09179 0.08657 -0.0216 0.0421 1.0000
13.000 1.0879 0.09812 0.09315 -0.0255 0.0426 1.0000
13.250 1.0526 0.10674 0.10197 -0.0317 0.0430 1.0000
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Polar data table (+)
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