GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il) Reynolds number: 100,000 Max Cl/Cd: 48.89 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe677-il-100000-n5.txt Download as CSV file: xf-goe677-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 677 (= M 6) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5532 0.09011 0.08504 -0.0207 1.0000 0.0522
-9.500 -0.5714 0.08158 0.07655 -0.0280 1.0000 0.0514
-9.250 -0.6055 0.07235 0.06724 -0.0334 1.0000 0.0506
-9.000 -0.6299 0.06584 0.06057 -0.0339 1.0000 0.0502
-8.750 -0.6423 0.06067 0.05520 -0.0333 1.0000 0.0503
-8.500 -0.6458 0.05668 0.05101 -0.0322 1.0000 0.0507
-8.250 -0.6424 0.05372 0.04788 -0.0309 1.0000 0.0517
-8.000 -0.6390 0.05056 0.04451 -0.0294 1.0000 0.0529
-7.750 -0.6358 0.04710 0.04075 -0.0275 1.0000 0.0539
-7.500 -0.6315 0.04366 0.03697 -0.0252 1.0000 0.0545
-7.250 -0.6253 0.04057 0.03352 -0.0228 1.0000 0.0551
-7.000 -0.6178 0.03790 0.03049 -0.0202 1.0000 0.0557
-6.750 -0.6098 0.03564 0.02789 -0.0175 1.0000 0.0565
-6.500 -0.5823 0.03315 0.02480 -0.0184 0.9879 0.0584
-6.250 -0.5507 0.03088 0.02221 -0.0201 0.9740 0.0599
-6.000 -0.5176 0.02911 0.02024 -0.0218 0.9600 0.0611
-5.750 -0.4841 0.02757 0.01848 -0.0234 0.9456 0.0624
-5.500 -0.4507 0.02620 0.01688 -0.0247 0.9310 0.0639
-5.250 -0.4178 0.02495 0.01540 -0.0258 0.9165 0.0657
-5.000 -0.3864 0.02396 0.01418 -0.0265 0.9021 0.0685
-4.750 -0.3562 0.02314 0.01310 -0.0268 0.8882 0.0711
-4.500 -0.3277 0.02204 0.01195 -0.0270 0.8751 0.0734
-4.250 -0.3003 0.02124 0.01112 -0.0269 0.8624 0.0757
-4.000 -0.2736 0.02056 0.01037 -0.0265 0.8501 0.0786
-3.750 -0.2477 0.01996 0.00967 -0.0260 0.8375 0.0820
-3.500 -0.2224 0.01942 0.00904 -0.0253 0.8248 0.0865
-3.250 -0.1981 0.01891 0.00854 -0.0246 0.8123 0.0919
-3.000 -0.1735 0.01847 0.00802 -0.0237 0.8002 0.0977
-2.750 -0.1492 0.01803 0.00756 -0.0229 0.7891 0.1041
-2.500 -0.1240 0.01770 0.00720 -0.0222 0.7782 0.1145
-2.250 -0.0986 0.01736 0.00684 -0.0216 0.7698 0.1276
-2.000 -0.0733 0.01696 0.00652 -0.0211 0.7613 0.1467
-1.750 -0.0484 0.01647 0.00618 -0.0206 0.7539 0.1846
-1.500 -0.0251 0.01564 0.00597 -0.0200 0.7459 0.3196
-1.250 0.0289 0.01443 0.00678 -0.0228 0.7399 0.8615
-1.000 0.0581 0.01485 0.00708 -0.0221 0.7317 0.9140
-0.750 0.1206 0.01542 0.00742 -0.0278 0.7248 0.9558
-0.500 0.2077 0.01561 0.00743 -0.0395 0.7157 0.9919
-0.250 0.2518 0.01551 0.00717 -0.0430 0.7083 1.0000
0.000 0.2768 0.01550 0.00708 -0.0427 0.6994 1.0000
0.250 0.3013 0.01550 0.00695 -0.0422 0.6920 1.0000
0.500 0.3263 0.01550 0.00691 -0.0418 0.6832 1.0000
0.750 0.3510 0.01553 0.00683 -0.0413 0.6758 1.0000
1.000 0.3760 0.01556 0.00682 -0.0409 0.6666 1.0000
1.250 0.4007 0.01559 0.00678 -0.0404 0.6586 1.0000
1.500 0.4255 0.01564 0.00680 -0.0400 0.6493 1.0000
1.750 0.4503 0.01569 0.00682 -0.0395 0.6408 1.0000
2.000 0.4750 0.01575 0.00684 -0.0390 0.6317 1.0000
2.250 0.4996 0.01582 0.00692 -0.0385 0.6221 1.0000
2.500 0.5240 0.01589 0.00693 -0.0378 0.6135 1.0000
2.750 0.5482 0.01599 0.00706 -0.0373 0.6028 1.0000
3.000 0.5724 0.01608 0.00715 -0.0366 0.5933 1.0000
3.250 0.5964 0.01616 0.00723 -0.0359 0.5830 1.0000
3.500 0.6201 0.01625 0.00736 -0.0352 0.5708 1.0000
3.750 0.6437 0.01633 0.00746 -0.0344 0.5584 1.0000
4.000 0.6670 0.01640 0.00754 -0.0336 0.5454 1.0000
4.250 0.6901 0.01647 0.00761 -0.0326 0.5312 1.0000
4.500 0.7129 0.01655 0.00771 -0.0317 0.5163 1.0000
4.750 0.7355 0.01664 0.00780 -0.0307 0.5012 1.0000
5.000 0.7579 0.01676 0.00791 -0.0296 0.4859 1.0000
5.250 0.7799 0.01692 0.00805 -0.0286 0.4705 1.0000
5.500 0.8017 0.01712 0.00823 -0.0274 0.4560 1.0000
5.750 0.8233 0.01737 0.00845 -0.0263 0.4422 1.0000
6.000 0.8444 0.01765 0.00871 -0.0251 0.4277 1.0000
6.250 0.8650 0.01796 0.00903 -0.0239 0.4122 1.0000
6.500 0.8855 0.01828 0.00938 -0.0226 0.3972 1.0000
6.750 0.9058 0.01861 0.00978 -0.0214 0.3827 1.0000
7.000 0.9256 0.01895 0.01020 -0.0200 0.3671 1.0000
7.250 0.9446 0.01932 0.01064 -0.0186 0.3495 1.0000
7.500 0.9629 0.01970 0.01110 -0.0170 0.3273 1.0000
7.750 0.9796 0.02015 0.01155 -0.0153 0.2999 1.0000
8.000 0.9941 0.02074 0.01206 -0.0132 0.2672 1.0000
8.250 1.0062 0.02152 0.01268 -0.0109 0.2348 1.0000
8.500 1.0168 0.02240 0.01347 -0.0084 0.2075 1.0000
8.750 1.0263 0.02337 0.01433 -0.0058 0.1864 1.0000
9.000 1.0354 0.02435 0.01525 -0.0033 0.1693 1.0000
9.250 1.0439 0.02536 0.01620 -0.0007 0.1549 1.0000
9.500 1.0522 0.02635 0.01718 0.0018 0.1424 1.0000
9.750 1.0610 0.02730 0.01814 0.0041 0.1311 1.0000
10.000 1.0683 0.02829 0.01918 0.0066 0.1219 1.0000
10.500 1.0771 0.03049 0.02142 0.0117 0.1059 1.0000
10.750 1.0806 0.03185 0.02279 0.0138 0.0985 1.0000
11.000 1.0851 0.03330 0.02430 0.0155 0.0916 1.0000
11.250 1.0888 0.03495 0.02600 0.0169 0.0862 1.0000
11.500 1.0944 0.03659 0.02777 0.0180 0.0794 1.0000
11.750 1.0969 0.03857 0.02984 0.0189 0.0727 1.0000
12.000 1.1016 0.04051 0.03193 0.0195 0.0639 1.0000
12.250 1.1064 0.04254 0.03410 0.0200 0.0545 1.0000
12.500 1.1080 0.04494 0.03656 0.0204 0.0474 1.0000
12.750 1.1070 0.04769 0.03930 0.0205 0.0427 1.0000
13.000 1.1061 0.05049 0.04219 0.0206 0.0389 1.0000
13.250 1.1029 0.05362 0.04535 0.0205 0.0364 1.0000
13.500 1.0998 0.05681 0.04862 0.0203 0.0344 1.0000
13.750 1.0968 0.06006 0.05199 0.0200 0.0325 1.0000
14.000 1.0926 0.06354 0.05557 0.0195 0.0312 1.0000
14.250 1.0872 0.06728 0.05941 0.0188 0.0303 1.0000
14.500 1.0809 0.07124 0.06345 0.0179 0.0296 1.0000
14.750 1.0770 0.07498 0.06731 0.0172 0.0288 1.0000
15.000 1.0736 0.07877 0.07126 0.0163 0.0281 1.0000
15.250 1.0698 0.08272 0.07536 0.0153 0.0274 1.0000
15.500 1.0655 0.08688 0.07966 0.0141 0.0268 1.0000
15.750 1.0604 0.09126 0.08418 0.0126 0.0261 1.0000
16.000 1.0546 0.09583 0.08887 0.0109 0.0255 1.0000
16.250 1.0486 0.10054 0.09370 0.0091 0.0250 1.0000
16.500 1.0424 0.10539 0.09864 0.0071 0.0246 1.0000
16.750 1.0364 0.11019 0.10352 0.0050 0.0241 1.0000
17.000 1.0307 0.11498 0.10838 0.0031 0.0237 1.0000
17.250 1.0213 0.12093 0.11452 0.0002 0.0234 1.0000
17.500 1.0105 0.12738 0.12116 -0.0030 0.0232 1.0000
17.750 0.9976 0.13454 0.12850 -0.0068 0.0231 1.0000
18.000 0.9820 0.14267 0.13681 -0.0113 0.0231 1.0000
18.250 0.9628 0.15228 0.14660 -0.0167 0.0231 1.0000
18.500 0.9359 0.16483 0.15933 -0.0238 0.0233 1.0000
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Polar data table (+)
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