GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il) Reynolds number: 500,000 Max Cl/Cd: 100.68 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe140-il-500000.txt Download as CSV file: xf-goe140-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 140 (MVA H.17) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2998 0.09797 0.09588 -0.0219 1.0000 0.0206
-8.000 -0.2996 0.09532 0.09326 -0.0243 1.0000 0.0207
-7.750 -0.2987 0.09248 0.09047 -0.0267 1.0000 0.0207
-7.500 -0.2950 0.08938 0.08740 -0.0290 1.0000 0.0207
-7.250 -0.2926 0.08498 0.08305 -0.0300 0.9992 0.0209
-7.000 -0.2741 0.08108 0.07914 -0.0303 0.9958 0.0213
-6.750 -0.2494 0.07729 0.07533 -0.0351 0.9896 0.0217
-6.500 -0.2221 0.07337 0.07139 -0.0413 0.9803 0.0224
-6.250 -0.1932 0.06932 0.06731 -0.0481 0.9671 0.0239
-6.000 -0.1436 0.06378 0.06161 -0.0640 0.9462 0.0260
-5.750 -0.1139 0.05950 0.05719 -0.0698 0.9251 0.0261
-5.500 -0.0960 0.05360 0.05116 -0.0735 0.9021 0.0265
-5.250 -0.0814 0.05112 0.04859 -0.0732 0.8793 0.0270
-5.000 -0.0624 0.04895 0.04631 -0.0738 0.8573 0.0276
-4.750 -0.0389 0.04649 0.04371 -0.0756 0.8372 0.0285
-4.500 -0.0117 0.04370 0.04073 -0.0782 0.8187 0.0299
-4.250 0.0326 0.04105 0.03770 -0.0826 0.8012 0.0330
-4.000 0.0631 0.03846 0.03486 -0.0844 0.7836 0.0331
-3.750 0.0849 0.03339 0.02962 -0.0868 0.7668 0.0343
-3.500 0.1096 0.03169 0.02779 -0.0875 0.7477 0.0350
-3.250 0.1364 0.03003 0.02596 -0.0884 0.7285 0.0362
-3.000 0.1653 0.02831 0.02402 -0.0893 0.7080 0.0381
-2.750 0.2014 0.02794 0.02322 -0.0892 0.6872 0.0418
-2.500 0.2300 0.02396 0.01890 -0.0910 0.6686 0.0431
-2.250 0.2565 0.02272 0.01754 -0.0916 0.6473 0.0442
-2.000 0.2842 0.02168 0.01633 -0.0920 0.6271 0.0456
-1.750 0.3133 0.02070 0.01513 -0.0924 0.6079 0.0484
-1.500 0.3463 0.01961 0.01352 -0.0924 0.5899 0.0533
-1.250 0.3739 0.01824 0.01206 -0.0930 0.5711 0.0547
-1.000 0.4020 0.01749 0.01117 -0.0934 0.5520 0.0564
-0.750 0.4307 0.01688 0.01037 -0.0936 0.5339 0.0593
-0.500 0.4605 0.01796 0.01115 -0.0929 0.5160 0.0640
0.000 0.5193 0.01531 0.00802 -0.0935 0.4857 0.0647
0.250 0.5505 0.01220 0.00452 -0.0934 0.4737 0.0422
0.500 0.5788 0.01158 0.00379 -0.0934 0.4607 0.0428
0.750 0.6072 0.01124 0.00338 -0.0936 0.4488 0.0437
1.000 0.6354 0.01115 0.00325 -0.0937 0.4377 0.0457
1.250 0.6636 0.01111 0.00315 -0.0937 0.4272 0.0476
1.500 0.6920 0.01104 0.00303 -0.0938 0.4171 0.0497
1.750 0.7203 0.01101 0.00296 -0.0939 0.4079 0.0527
2.000 0.7484 0.01104 0.00296 -0.0940 0.3988 0.0609
2.250 0.7768 0.01101 0.00295 -0.0941 0.3898 0.0815
2.500 0.8048 0.01107 0.00299 -0.0942 0.3814 0.0988
2.750 0.8328 0.01113 0.00306 -0.0943 0.3734 0.1152
3.000 0.8585 0.00985 0.00336 -0.0946 0.3669 0.8137
3.250 0.8822 0.00965 0.00336 -0.0934 0.3603 1.0000
3.500 0.9097 0.00987 0.00348 -0.0933 0.3540 1.0000
3.750 0.9376 0.01001 0.00359 -0.0934 0.3478 1.0000
4.000 0.9650 0.01022 0.00373 -0.0934 0.3415 1.0000
4.250 0.9926 0.01039 0.00389 -0.0934 0.3352 1.0000
4.500 1.0198 0.01059 0.00402 -0.0933 0.3267 1.0000
4.750 1.0473 0.01074 0.00416 -0.0934 0.3182 1.0000
5.000 1.0741 0.01098 0.00434 -0.0933 0.3106 1.0000
5.250 1.1016 0.01112 0.00450 -0.0933 0.3037 1.0000
5.500 1.1283 0.01134 0.00466 -0.0933 0.2933 1.0000
5.750 1.1551 0.01155 0.00483 -0.0932 0.2831 1.0000
6.000 1.1819 0.01175 0.00503 -0.0932 0.2727 1.0000
6.250 1.2082 0.01200 0.00523 -0.0930 0.2589 1.0000
6.500 1.2335 0.01238 0.00548 -0.0928 0.2381 1.0000
6.750 1.2577 0.01291 0.00583 -0.0925 0.2053 1.0000
7.000 1.2713 0.01485 0.00709 -0.0910 0.0976 1.0000
7.250 1.2853 0.01668 0.00845 -0.0894 0.0225 1.0000
7.500 1.3089 0.01719 0.00899 -0.0888 0.0188 1.0000
7.750 1.3318 0.01775 0.00965 -0.0881 0.0174 1.0000
8.000 1.3536 0.01840 0.01042 -0.0873 0.0163 1.0000
8.250 1.3743 0.01915 0.01127 -0.0864 0.0154 1.0000
8.500 1.3928 0.02008 0.01233 -0.0851 0.0148 1.0000
8.750 1.4100 0.02105 0.01341 -0.0837 0.0144 1.0000
9.000 1.4271 0.02195 0.01440 -0.0823 0.0142 1.0000
9.250 1.4421 0.02296 0.01552 -0.0807 0.0138 1.0000
9.500 1.4548 0.02405 0.01670 -0.0787 0.0133 1.0000
9.750 1.4638 0.02527 0.01801 -0.0763 0.0129 1.0000
10.000 1.4666 0.02660 0.01943 -0.0730 0.0126 1.0000
10.250 1.4670 0.02817 0.02110 -0.0698 0.0124 1.0000
10.500 1.4664 0.03003 0.02308 -0.0671 0.0122 1.0000
10.750 1.4647 0.03226 0.02541 -0.0650 0.0121 1.0000
11.000 1.4621 0.03488 0.02814 -0.0635 0.0120 1.0000
11.250 1.4586 0.03788 0.03125 -0.0626 0.0118 1.0000
11.500 1.4551 0.04110 0.03458 -0.0621 0.0118 1.0000
11.750 1.4508 0.04458 0.03815 -0.0618 0.0117 1.0000
12.000 1.4468 0.04808 0.04173 -0.0616 0.0116 1.0000
12.250 1.4434 0.05153 0.04525 -0.0613 0.0115 1.0000
12.500 1.4412 0.05477 0.04856 -0.0609 0.0115 1.0000
12.750 1.4405 0.05776 0.05162 -0.0604 0.0115 1.0000
13.000 1.4414 0.06049 0.05440 -0.0596 0.0115 1.0000
13.250 1.4441 0.06307 0.05706 -0.0589 0.0116 1.0000
13.500 1.4471 0.06571 0.05984 -0.0583 0.0119 1.0000
13.750 1.4503 0.06826 0.06250 -0.0574 0.0121 1.0000
14.000 1.4541 0.07066 0.06499 -0.0565 0.0121 1.0000
14.250 1.4577 0.07322 0.06767 -0.0556 0.0124 1.0000
14.500 1.5082 0.06996 0.06472 -0.0491 0.0210 1.0000
14.750 1.5198 0.07173 0.06647 -0.0470 0.0201 1.0000
15.000 1.4986 0.07783 0.07283 -0.0475 0.0184 1.0000
15.250 1.4904 0.08207 0.07724 -0.0488 0.0181 1.0000
15.500 1.4831 0.08645 0.08177 -0.0500 0.0178 1.0000
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Polar data table (+)
Polar graphs
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