GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 14K AIRFOIL (goe14k-il) Reynolds number: 200,000 Max Cl/Cd: 60.78 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe14k-il-200000.txt Download as CSV file: xf-goe14k-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6035 0.09265 0.08949 -0.0346 0.9962 0.0622
-8.500 -0.6221 0.08652 0.08332 -0.0393 0.9918 0.0630
-8.250 -0.6497 0.08286 0.07963 -0.0372 0.9893 0.0630
-8.000 -0.6743 0.07898 0.07568 -0.0346 0.9875 0.0638
-7.750 -0.6908 0.07365 0.07015 -0.0336 0.9827 0.0650
-7.500 -0.7175 0.06976 0.06601 -0.0281 0.9825 0.0665
-6.750 -0.8300 0.04869 0.04366 0.0014 0.9943 0.0419
-6.500 -0.8355 0.04509 0.03966 0.0070 0.9939 0.0415
-6.250 -0.8348 0.04187 0.03599 0.0119 0.9920 0.0418
-6.000 -0.8263 0.03960 0.03322 0.0156 0.9893 0.0432
-5.750 -0.8135 0.03860 0.03162 0.0191 0.9869 0.0448
-5.500 -0.8010 0.03510 0.02769 0.0217 0.9853 0.0458
-5.250 -0.7899 0.03357 0.02602 0.0247 0.9849 0.0470
-5.000 -0.7761 0.03284 0.02530 0.0269 0.9835 0.0496
-4.750 -0.7562 0.03173 0.02392 0.0285 0.9797 0.0519
-4.500 -0.7287 0.03121 0.02301 0.0289 0.9764 0.0547
-4.250 -0.7000 0.02984 0.02141 0.0285 0.9746 0.0579
-4.000 -0.6851 0.02905 0.02060 0.0307 0.9740 0.0617
-3.750 -0.6120 0.02843 0.01964 0.0221 0.9487 0.0680
-3.500 -0.5858 0.02708 0.01834 0.0220 0.9452 0.0744
-3.250 -0.5532 0.02675 0.01792 0.0209 0.9417 0.0798
-3.000 -0.5160 0.02610 0.01726 0.0188 0.9370 0.0859
-2.750 -0.4985 0.02567 0.01684 0.0206 0.9332 0.0913
-2.500 -0.4715 0.02538 0.01652 0.0206 0.9301 0.0975
-2.250 -0.4365 0.02523 0.01641 0.0188 0.9273 0.1053
-2.000 -0.4151 0.02491 0.01612 0.0199 0.9222 0.1142
-1.750 -0.3934 0.02469 0.01594 0.0209 0.9186 0.1266
-1.500 -0.1160 0.02427 0.01910 -0.0350 0.9318 0.9502
-1.250 0.0039 0.02629 0.02088 -0.0546 0.9359 0.9968
-1.000 0.0402 0.02649 0.02098 -0.0570 0.9335 1.0000
-0.750 0.0647 0.02658 0.02098 -0.0569 0.9300 1.0000
-0.500 0.0940 0.02675 0.02106 -0.0577 0.9277 1.0000
-0.250 0.1288 0.02699 0.02122 -0.0595 0.9259 1.0000
0.000 0.1325 0.02699 0.02117 -0.0552 0.9189 1.0000
0.250 0.1595 0.02714 0.02128 -0.0555 0.9158 1.0000
0.500 0.1935 0.02731 0.02140 -0.0572 0.9134 1.0000
0.750 0.2078 0.02738 0.02145 -0.0549 0.9064 1.0000
1.000 0.2397 0.02738 0.02142 -0.0560 0.9018 1.0000
1.250 0.2837 0.02734 0.02135 -0.0594 0.8989 1.0000
1.500 0.2938 0.02743 0.02144 -0.0562 0.8905 1.0000
1.750 0.3295 0.02737 0.02139 -0.0580 0.8867 1.0000
2.000 0.3697 0.02733 0.02136 -0.0606 0.8844 1.0000
2.250 0.3803 0.02742 0.02146 -0.0575 0.8749 1.0000
2.500 0.4186 0.02726 0.02133 -0.0596 0.8715 1.0000
2.750 0.4630 0.02690 0.02102 -0.0627 0.8682 1.0000
3.000 0.4777 0.02688 0.02104 -0.0602 0.8585 1.0000
3.250 0.5466 0.02545 0.01969 -0.0673 0.8549 1.0000
3.500 0.5931 0.02388 0.01819 -0.0696 0.8426 1.0000
3.750 0.6965 0.02034 0.01480 -0.0821 0.8394 1.0000
4.000 0.7134 0.01990 0.01443 -0.0793 0.8277 1.0000
4.250 0.7532 0.01865 0.01331 -0.0805 0.8187 1.0000
5.000 0.8473 0.01567 0.01059 -0.0793 0.7630 1.0000
5.250 0.8965 0.01475 0.00848 -0.0816 0.5194 1.0000
5.500 0.8721 0.01605 0.00914 -0.0708 0.4192 1.0000
5.750 0.8573 0.01728 0.00988 -0.0625 0.3302 1.0000
6.000 0.8451 0.01871 0.01066 -0.0551 0.2220 1.0000
6.250 0.8429 0.01999 0.01147 -0.0498 0.1558 1.0000
6.500 0.8491 0.02092 0.01218 -0.0460 0.1266 1.0000
6.750 0.8589 0.02168 0.01286 -0.0428 0.1110 1.0000
7.000 0.8695 0.02245 0.01357 -0.0399 0.0989 1.0000
7.250 0.8828 0.02310 0.01425 -0.0373 0.0895 1.0000
7.500 0.8940 0.02403 0.01514 -0.0345 0.0808 1.0000
7.750 0.9072 0.02485 0.01594 -0.0321 0.0734 1.0000
8.000 0.9225 0.02578 0.01691 -0.0301 0.0662 1.0000
8.250 0.9392 0.02675 0.01782 -0.0284 0.0605 1.0000
8.500 0.9624 0.02783 0.01897 -0.0277 0.0559 1.0000
8.750 0.9795 0.02854 0.01973 -0.0260 0.0517 1.0000
9.000 1.0186 0.03037 0.02153 -0.0284 0.0475 1.0000
9.250 1.0394 0.03129 0.02264 -0.0272 0.0451 1.0000
9.500 1.0569 0.03218 0.02363 -0.0256 0.0421 1.0000
9.750 1.0781 0.03329 0.02475 -0.0249 0.0400 1.0000
10.000 1.1215 0.03631 0.02802 -0.0282 0.0379 1.0000
10.250 1.1397 0.03823 0.03028 -0.0266 0.0370 1.0000
10.500 1.1465 0.03952 0.03181 -0.0230 0.0352 1.0000
10.750 1.1575 0.04152 0.03408 -0.0205 0.0343 1.0000
11.000 1.1654 0.04305 0.03575 -0.0176 0.0333 1.0000
11.250 1.1717 0.04478 0.03762 -0.0146 0.0325 1.0000
11.500 1.1748 0.04705 0.04011 -0.0112 0.0320 1.0000
11.750 1.1743 0.04957 0.04285 -0.0075 0.0317 1.0000
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Polar data table (+)
Polar graphs
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