GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 406 AIRFOIL (goe406-il) Reynolds number: 100,000 Max Cl/Cd: 54.15 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe406-il-100000.txt Download as CSV file: xf-goe406-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 406 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2930 0.11585 0.11136 -0.0276 1.0000 0.0699
-8.750 -0.3090 0.11557 0.11117 -0.0243 1.0000 0.0704
-8.500 -0.3230 0.11500 0.11069 -0.0217 1.0000 0.0709
-8.250 -0.3089 0.11172 0.10739 -0.0264 0.9952 0.0730
-8.000 -0.2986 0.10902 0.10470 -0.0336 0.9874 0.0753
-7.750 -0.3063 0.10820 0.10388 -0.0430 0.9751 0.0763
-7.500 -0.2996 0.10513 0.10077 -0.0517 0.9637 0.0767
-7.250 -0.2635 0.09812 0.09380 -0.0458 0.9658 0.0790
-7.000 -0.2448 0.09469 0.09036 -0.0483 0.9598 0.0814
-6.750 -0.2375 0.09204 0.08771 -0.0506 0.9509 0.0834
-6.500 -0.2201 0.08875 0.08435 -0.0594 0.9428 0.0877
-6.250 -0.2183 0.08797 0.08327 -0.0688 0.9284 0.0893
-6.000 -0.2100 0.08279 0.07826 -0.0653 0.9228 0.0903
-5.750 -0.1943 0.07926 0.07477 -0.0643 0.9175 0.0919
-5.500 -0.1699 0.07581 0.07130 -0.0668 0.9134 0.0951
-5.250 -0.1679 0.07393 0.06938 -0.0660 0.9037 0.0978
-5.000 -0.1523 0.07344 0.06837 -0.0725 0.8942 0.1038
-4.750 -0.1432 0.06888 0.06399 -0.0708 0.8882 0.1050
-4.500 -0.1207 0.06540 0.06056 -0.0713 0.8842 0.1078
-4.250 -0.1124 0.06363 0.05875 -0.0700 0.8768 0.1117
-4.000 -0.0926 0.06193 0.05667 -0.0725 0.8695 0.1204
-3.750 -0.0649 0.05810 0.05295 -0.0737 0.8667 0.1246
-3.500 -0.0660 0.05716 0.05196 -0.0701 0.8563 0.1290
-3.250 -0.0325 0.05412 0.04866 -0.0730 0.8516 0.1387
-3.000 -0.0230 0.05246 0.04699 -0.0706 0.8411 0.1440
-2.750 0.0179 0.04914 0.04345 -0.0736 0.8357 0.1576
-2.500 0.0301 0.04795 0.04204 -0.0715 0.8246 0.1710
-2.250 0.0681 0.04482 0.03883 -0.0735 0.8199 0.1894
-2.000 0.1108 0.04214 0.03599 -0.0762 0.8174 0.2228
-1.750 0.1036 0.04155 0.03547 -0.0705 0.8051 0.2283
-0.250 0.3262 0.03082 0.02221 -0.0729 0.7692 0.1164
0.000 0.3833 0.02867 0.01954 -0.0764 0.7658 0.1050
0.250 0.3946 0.02852 0.01926 -0.0728 0.7543 0.1044
0.500 0.4501 0.02688 0.01740 -0.0767 0.7494 0.1032
0.750 0.4737 0.02623 0.01669 -0.0754 0.7390 0.1028
1.000 0.5265 0.02480 0.01515 -0.0790 0.7322 0.1036
1.250 0.5552 0.02400 0.01445 -0.0789 0.7213 0.1070
1.500 0.6055 0.02287 0.01329 -0.0822 0.7137 0.1180
1.750 0.6393 0.02235 0.01281 -0.0831 0.7009 0.1302
2.000 0.8520 0.01898 0.01089 -0.1208 0.6834 1.0000
2.250 0.8751 0.01896 0.01074 -0.1193 0.6691 1.0000
2.500 0.8991 0.01890 0.01055 -0.1180 0.6543 1.0000
2.750 0.9225 0.01884 0.01035 -0.1166 0.6381 1.0000
3.000 0.9446 0.01882 0.01020 -0.1149 0.6207 1.0000
3.250 0.9660 0.01884 0.01009 -0.1132 0.6022 1.0000
3.500 0.9876 0.01891 0.01003 -0.1115 0.5838 1.0000
3.750 1.0091 0.01906 0.01002 -0.1100 0.5659 1.0000
4.000 1.0304 0.01929 0.01011 -0.1085 0.5490 1.0000
4.250 1.0515 0.01958 0.01029 -0.1070 0.5334 1.0000
4.500 1.0727 0.01993 0.01052 -0.1056 0.5194 1.0000
4.750 1.0953 0.02030 0.01076 -0.1045 0.5072 1.0000
5.000 1.1192 0.02067 0.01100 -0.1038 0.4963 1.0000
5.250 1.1384 0.02119 0.01152 -0.1022 0.4854 1.0000
5.500 1.1640 0.02165 0.01186 -0.1018 0.4773 1.0000
5.750 1.1837 0.02222 0.01246 -0.1004 0.4687 1.0000
6.000 1.2119 0.02273 0.01285 -0.1006 0.4622 1.0000
6.250 1.2284 0.02340 0.01364 -0.0987 0.4549 1.0000
6.500 1.2542 0.02393 0.01411 -0.0985 0.4486 1.0000
6.750 1.2750 0.02462 0.01487 -0.0974 0.4428 1.0000
7.000 1.2936 0.02533 0.01567 -0.0960 0.4370 1.0000
7.250 1.3199 0.02596 0.01628 -0.0959 0.4323 1.0000
7.500 1.3425 0.02677 0.01714 -0.0953 0.4280 1.0000
7.750 1.3566 0.02767 0.01825 -0.0931 0.4235 1.0000
8.000 1.3762 0.02849 0.01917 -0.0920 0.4192 1.0000
8.250 1.4035 0.02919 0.01987 -0.0922 0.4152 1.0000
8.500 1.4206 0.03019 0.02101 -0.0907 0.4112 1.0000
8.750 1.4306 0.03132 0.02238 -0.0880 0.4074 1.0000
9.000 1.4471 0.03221 0.02340 -0.0864 0.4028 1.0000
9.250 1.4810 0.03266 0.02374 -0.0876 0.3967 1.0000
9.500 1.4789 0.03378 0.02515 -0.0828 0.3908 1.0000
9.750 1.5139 0.03367 0.02488 -0.0839 0.3810 1.0000
10.000 1.5105 0.03469 0.02618 -0.0789 0.3743 1.0000
10.250 1.5441 0.03456 0.02589 -0.0797 0.3646 1.0000
10.500 1.5399 0.03561 0.02722 -0.0747 0.3585 1.0000
10.750 1.5615 0.03570 0.02729 -0.0736 0.3497 1.0000
11.000 1.5652 0.03646 0.02821 -0.0699 0.3426 1.0000
11.250 1.5759 0.03683 0.02866 -0.0671 0.3349 1.0000
11.500 1.5874 0.03728 0.02918 -0.0646 0.3273 1.0000
11.750 1.5851 0.03784 0.02991 -0.0598 0.3199 1.0000
12.000 1.5929 0.03792 0.02999 -0.0565 0.3111 1.0000
12.250 1.5809 0.03858 0.03082 -0.0504 0.3042 1.0000
12.500 1.5848 0.03865 0.03091 -0.0468 0.2951 1.0000
12.750 1.5705 0.03962 0.03208 -0.0412 0.2876 1.0000
13.000 1.5661 0.04016 0.03269 -0.0371 0.2785 1.0000
13.250 1.5522 0.04139 0.03410 -0.0326 0.2694 1.0000
13.500 1.5351 0.04315 0.03604 -0.0285 0.2596 1.0000
13.750 1.5191 0.04509 0.03809 -0.0251 0.2477 1.0000
14.000 1.4979 0.04799 0.04115 -0.0223 0.2335 1.0000
14.250 1.4739 0.05186 0.04522 -0.0203 0.2153 1.0000
14.500 1.4490 0.05637 0.04976 -0.0190 0.1918 1.0000
14.750 1.4190 0.06200 0.05527 -0.0184 0.1608 1.0000
15.000 1.3891 0.06818 0.06130 -0.0183 0.1434 1.0000
15.250 1.3588 0.07495 0.06798 -0.0189 0.1323 1.0000
15.500 1.3294 0.08201 0.07498 -0.0199 0.1239 1.0000
15.750 1.3012 0.08916 0.08204 -0.0212 0.1162 1.0000
16.000 1.2815 0.09522 0.08808 -0.0222 0.1086 1.0000
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Polar data table (+)
Polar graphs
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