GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il) Reynolds number: 200,000 Max Cl/Cd: 79.75 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe121-il-200000.txt Download as CSV file: xf-goe121-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 121 (MVA H.1) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3521 0.09737 0.09380 -0.0228 1.0000 0.0467
-7.750 -0.3601 0.09655 0.09308 -0.0262 1.0000 0.0473
-7.500 -0.3559 0.09421 0.09078 -0.0317 1.0000 0.0476
-7.250 -0.3535 0.08941 0.08603 -0.0320 1.0000 0.0481
-7.000 -0.3474 0.08572 0.08237 -0.0270 1.0000 0.0490
-6.750 -0.3415 0.08313 0.07981 -0.0252 1.0000 0.0500
-6.500 -0.3377 0.08088 0.07761 -0.0246 1.0000 0.0512
-6.250 -0.3363 0.07885 0.07562 -0.0242 1.0000 0.0529
-6.000 -0.3363 0.07685 0.07365 -0.0242 1.0000 0.0550
-5.750 -0.3173 0.07481 0.07153 -0.0374 1.0000 0.0586
-5.500 -0.3138 0.07055 0.06728 -0.0383 1.0000 0.0592
-5.250 -0.3043 0.06712 0.06389 -0.0361 0.9982 0.0601
-5.000 -0.2767 0.06383 0.06058 -0.0385 0.9948 0.0620
-4.750 -0.2381 0.06004 0.05672 -0.0454 0.9900 0.0662
-4.500 -0.1797 0.05394 0.05038 -0.0597 0.9854 0.0720
-4.250 -0.1498 0.05106 0.04748 -0.0623 0.9810 0.0741
-4.000 -0.0792 0.04623 0.04211 -0.0770 0.9756 0.0831
-3.750 -0.0487 0.04234 0.03831 -0.0797 0.9722 0.0845
-3.500 -0.0168 0.04002 0.03598 -0.0819 0.9651 0.0876
-3.250 0.0456 0.03577 0.03116 -0.0916 0.9608 0.0968
-3.000 0.0828 0.03264 0.02805 -0.0950 0.9567 0.0983
-2.750 0.1366 0.02390 0.01832 -0.1015 0.9517 0.0688
-2.500 0.1811 0.02070 0.01471 -0.1053 0.9477 0.0673
-2.250 0.2253 0.01788 0.01139 -0.1086 0.9445 0.0661
-2.000 0.2606 0.01602 0.00915 -0.1098 0.9365 0.0660
-1.750 0.3002 0.01464 0.00750 -0.1117 0.9312 0.0676
-1.500 0.3337 0.01376 0.00642 -0.1124 0.9218 0.0699
-1.250 0.3683 0.01305 0.00572 -0.1134 0.9133 0.0740
-1.000 0.3998 0.01278 0.00538 -0.1135 0.9021 0.0817
-0.750 0.4284 0.01240 0.00503 -0.1132 0.8892 0.0915
-0.500 0.4562 0.01191 0.00458 -0.1127 0.8764 0.1179
-0.250 0.4833 0.01166 0.00431 -0.1122 0.8635 0.1393
0.000 0.5100 0.01151 0.00417 -0.1117 0.8506 0.1535
0.250 0.5364 0.01139 0.00408 -0.1110 0.8363 0.1684
0.500 0.5624 0.01126 0.00397 -0.1102 0.8194 0.1821
0.750 0.5884 0.01109 0.00383 -0.1094 0.8006 0.1944
1.000 0.6146 0.01094 0.00367 -0.1085 0.7807 0.2056
1.250 0.6406 0.01083 0.00355 -0.1077 0.7579 0.2197
1.500 0.6668 0.01073 0.00348 -0.1069 0.7354 0.2535
1.750 0.6869 0.00918 0.00344 -0.1049 0.7136 1.0000
2.000 0.7131 0.00935 0.00340 -0.1041 0.6902 1.0000
2.250 0.7390 0.00951 0.00342 -0.1034 0.6624 1.0000
2.500 0.7645 0.00968 0.00343 -0.1026 0.6289 1.0000
2.750 0.7895 0.00990 0.00346 -0.1017 0.5909 1.0000
3.000 0.8139 0.01024 0.00354 -0.1008 0.5572 1.0000
3.250 0.8385 0.01063 0.00371 -0.1000 0.5287 1.0000
3.500 0.8635 0.01101 0.00394 -0.0994 0.5044 1.0000
3.750 0.8888 0.01138 0.00420 -0.0988 0.4836 1.0000
4.000 0.9143 0.01172 0.00445 -0.0983 0.4660 1.0000
4.250 0.9400 0.01203 0.00472 -0.0978 0.4496 1.0000
4.500 0.9658 0.01233 0.00499 -0.0973 0.4342 1.0000
4.750 0.9913 0.01262 0.00528 -0.0968 0.4178 1.0000
5.000 1.0162 0.01292 0.00554 -0.0962 0.3970 1.0000
5.250 1.0404 0.01328 0.00581 -0.0956 0.3754 1.0000
5.500 1.0649 0.01362 0.00612 -0.0949 0.3531 1.0000
5.750 1.0885 0.01404 0.00647 -0.0942 0.3304 1.0000
6.000 1.1127 0.01442 0.00683 -0.0936 0.3063 1.0000
6.250 1.1366 0.01481 0.00720 -0.0929 0.2803 1.0000
6.500 1.1594 0.01533 0.00757 -0.0921 0.2345 1.0000
6.750 1.1769 0.01652 0.00831 -0.0907 0.1681 1.0000
7.000 1.1901 0.01844 0.00962 -0.0887 0.0731 1.0000
7.250 1.2089 0.01964 0.01073 -0.0872 0.0489 1.0000
7.500 1.2286 0.02066 0.01175 -0.0859 0.0417 1.0000
7.750 1.2453 0.02195 0.01310 -0.0841 0.0376 1.0000
8.000 1.2620 0.02314 0.01445 -0.0823 0.0359 1.0000
8.250 1.2773 0.02442 0.01585 -0.0804 0.0345 1.0000
8.500 1.2913 0.02581 0.01732 -0.0783 0.0332 1.0000
8.750 1.3046 0.02728 0.01885 -0.0762 0.0316 1.0000
9.000 1.3157 0.02916 0.02074 -0.0740 0.0300 1.0000
9.250 1.3289 0.03174 0.02335 -0.0720 0.0291 1.0000
9.500 1.3476 0.03396 0.02568 -0.0707 0.0286 1.0000
9.750 1.3667 0.03588 0.02776 -0.0694 0.0283 1.0000
10.000 1.3857 0.03817 0.03024 -0.0681 0.0281 1.0000
10.250 1.4028 0.04066 0.03297 -0.0666 0.0279 1.0000
10.500 1.4155 0.04288 0.03546 -0.0647 0.0274 1.0000
10.750 1.4250 0.04525 0.03812 -0.0625 0.0269 1.0000
11.000 1.4316 0.04816 0.04135 -0.0601 0.0268 1.0000
11.250 1.4341 0.05171 0.04522 -0.0576 0.0272 1.0000
11.500 1.4309 0.05552 0.04933 -0.0546 0.0276 1.0000
11.750 1.4458 0.06113 0.05512 -0.0542 0.0292 1.0000
12.000 1.4231 0.06195 0.05644 -0.0481 0.0310 1.0000
12.250 1.3838 0.06867 0.06375 -0.0443 0.0344 1.0000
12.500 1.3657 0.07422 0.06950 -0.0432 0.0358 1.0000
12.750 1.2692 0.06653 0.06156 -0.0305 0.0297 1.0000
13.000 1.2383 0.07130 0.06665 -0.0295 0.0305 1.0000
13.250 1.2013 0.07746 0.07310 -0.0299 0.0309 1.0000
13.500 1.1645 0.08418 0.08008 -0.0314 0.0312 1.0000
13.750 1.1300 0.09091 0.08702 -0.0337 0.0315 1.0000
14.000 1.0950 0.09787 0.09416 -0.0368 0.0317 1.0000
14.250 1.0581 0.10421 0.10066 -0.0399 0.0317 1.0000
14.500 1.0196 0.11189 0.10851 -0.0446 0.0319 1.0000
14.750 0.9633 0.12429 0.12114 -0.0531 0.0333 1.0000
15.000 0.9187 0.13596 0.13290 -0.0601 0.0357 1.0000
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Polar data table (+)
Polar graphs
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