GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 7K AIRFOIL (goe07k-il) Reynolds number: 100,000 Max Cl/Cd: 40.69 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe07k-il-100000-n5.txt Download as CSV file: xf-goe07k-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 7K 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3071 0.10283 0.09798 -0.0731 0.9492 0.0462
-8.000 -0.3095 0.09938 0.09457 -0.0780 0.9454 0.0470
-7.750 -0.3190 0.09710 0.09233 -0.0763 0.9395 0.0469
-7.250 -0.3147 0.08797 0.08318 -0.0776 0.9323 0.0329
-7.000 -0.3200 0.08483 0.08005 -0.0773 0.9265 0.0313
-6.750 -0.3220 0.08063 0.07584 -0.0786 0.9210 0.0296
-6.500 -0.3145 0.07488 0.07000 -0.0829 0.9173 0.0275
-6.000 -0.3085 0.06419 0.05889 -0.0846 0.9054 0.0240
-5.750 -0.2959 0.05964 0.05411 -0.0856 0.9028 0.0239
-5.500 -0.2939 0.05632 0.05058 -0.0834 0.8979 0.0240
-5.250 -0.2896 0.05243 0.04643 -0.0816 0.8931 0.0245
-5.000 -0.2771 0.04902 0.04277 -0.0812 0.8902 0.0255
-4.750 -0.2588 0.04549 0.03885 -0.0808 0.8881 0.0257
-4.500 -0.2509 0.04301 0.03604 -0.0779 0.8841 0.0261
-4.250 -0.2411 0.04068 0.03332 -0.0750 0.8801 0.0262
-4.000 -0.2232 0.03887 0.03118 -0.0737 0.8774 0.0276
-3.750 -0.2011 0.03703 0.02894 -0.0728 0.8753 0.0297
-3.500 -0.1766 0.03473 0.02606 -0.0718 0.8737 0.0317
-3.250 -0.1581 0.03307 0.02389 -0.0696 0.8708 0.0337
-3.000 -0.1444 0.03209 0.02249 -0.0666 0.8667 0.0364
-2.750 -0.1235 0.03116 0.02144 -0.0656 0.8641 0.0396
-2.500 -0.0984 0.03046 0.02048 -0.0650 0.8621 0.0454
-2.250 -0.0713 0.02951 0.01936 -0.0649 0.8605 0.0515
-2.000 -0.0425 0.02895 0.01857 -0.0650 0.8591 0.0601
-1.750 -0.0312 0.02859 0.01828 -0.0623 0.8546 0.0678
-1.500 -0.0145 0.02829 0.01791 -0.0604 0.8512 0.0761
-1.250 0.0078 0.02802 0.01757 -0.0595 0.8487 0.0854
-1.000 0.0335 0.02772 0.01722 -0.0593 0.8467 0.0965
-0.750 0.0623 0.02750 0.01688 -0.0596 0.8451 0.1067
-0.500 0.2124 0.02566 0.01779 -0.0880 0.8520 1.0000
-0.250 0.2354 0.02590 0.01779 -0.0874 0.8489 1.0000
0.000 0.2614 0.02611 0.01780 -0.0873 0.8467 1.0000
0.250 0.2899 0.02630 0.01780 -0.0877 0.8450 1.0000
0.500 0.3008 0.02676 0.01816 -0.0850 0.8396 1.0000
0.750 0.3198 0.02711 0.01838 -0.0837 0.8357 1.0000
1.000 0.3458 0.02733 0.01849 -0.0837 0.8330 1.0000
1.250 0.3751 0.02749 0.01855 -0.0843 0.8310 1.0000
1.750 0.4109 0.02813 0.01907 -0.0812 0.8204 1.0000
2.000 0.4412 0.02818 0.01906 -0.0819 0.8175 1.0000
2.250 0.4752 0.02814 0.01899 -0.0832 0.8155 1.0000
2.500 0.4808 0.02873 0.01957 -0.0795 0.8068 1.0000
2.750 0.5100 0.02879 0.01963 -0.0800 0.8036 1.0000
3.000 0.5431 0.02875 0.01960 -0.0811 0.8014 1.0000
3.250 0.5505 0.02935 0.02022 -0.0778 0.7927 1.0000
3.500 0.5795 0.02940 0.02030 -0.0782 0.7892 1.0000
3.750 0.6120 0.02935 0.02031 -0.0792 0.7869 1.0000
4.000 0.6205 0.02995 0.02096 -0.0762 0.7778 1.0000
4.250 0.6501 0.02994 0.02105 -0.0766 0.7743 1.0000
4.500 0.6835 0.02980 0.02100 -0.0776 0.7719 1.0000
4.750 0.6917 0.03045 0.02173 -0.0746 0.7618 1.0000
5.000 0.7233 0.03031 0.02173 -0.0752 0.7585 1.0000
5.250 0.7377 0.03072 0.02224 -0.0732 0.7494 1.0000
5.500 0.7699 0.03034 0.02203 -0.0737 0.7444 1.0000
5.750 0.7885 0.03040 0.02222 -0.0720 0.7343 1.0000
7.250 0.9195 0.02735 0.02023 -0.0614 0.6300 1.0000
7.500 0.9765 0.02400 0.01540 -0.0613 0.3844 1.0000
7.750 0.9659 0.02605 0.01656 -0.0555 0.2506 1.0000
8.000 0.9648 0.02790 0.01776 -0.0517 0.1468 1.0000
8.250 0.9660 0.02977 0.01907 -0.0482 0.0764 1.0000
8.500 0.9727 0.03126 0.02048 -0.0453 0.0516 1.0000
8.750 0.9810 0.03261 0.02184 -0.0426 0.0409 1.0000
9.000 0.9890 0.03398 0.02325 -0.0400 0.0348 1.0000
9.250 0.9975 0.03533 0.02476 -0.0375 0.0312 1.0000
9.500 1.0049 0.03680 0.02631 -0.0350 0.0282 1.0000
9.750 1.0106 0.03859 0.02816 -0.0324 0.0258 1.0000
10.000 1.0231 0.04006 0.02983 -0.0304 0.0241 1.0000
10.250 1.0385 0.04152 0.03144 -0.0288 0.0222 1.0000
10.500 1.0543 0.04301 0.03302 -0.0275 0.0204 1.0000
10.750 1.0754 0.04489 0.03498 -0.0268 0.0191 1.0000
11.000 1.1096 0.04764 0.03796 -0.0274 0.0182 1.0000
11.250 1.1275 0.04982 0.04055 -0.0261 0.0173 1.0000
11.500 1.1408 0.05242 0.04354 -0.0244 0.0164 1.0000
11.750 1.1470 0.05490 0.04632 -0.0222 0.0157 1.0000
12.000 1.1497 0.05776 0.04950 -0.0196 0.0153 1.0000
12.250 1.1477 0.06081 0.05289 -0.0169 0.0152 1.0000
12.500 1.1414 0.06405 0.05645 -0.0139 0.0151 1.0000
12.750 1.1320 0.06741 0.06010 -0.0110 0.0150 1.0000
13.000 1.1182 0.07120 0.06423 -0.0082 0.0151 1.0000
13.250 1.1027 0.07507 0.06837 -0.0058 0.0150 1.0000
13.500 1.0852 0.07926 0.07283 -0.0038 0.0150 1.0000
13.750 1.0657 0.08382 0.07765 -0.0024 0.0151 1.0000
14.000 1.0441 0.08893 0.08301 -0.0018 0.0152 1.0000
14.250 1.0216 0.09454 0.08884 -0.0020 0.0153 1.0000
14.500 0.9990 0.10066 0.09517 -0.0033 0.0154 1.0000
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Polar data table (+)
Polar graphs
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