GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il) Reynolds number: 500,000 Max Cl/Cd: 104.29 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe137-il-500000.txt Download as CSV file: xf-goe137-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 137 (MVA H.15) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3468 0.08580 0.08372 -0.0239 1.0000 0.0203
-7.500 -0.3451 0.08280 0.08077 -0.0254 1.0000 0.0209
-7.250 -0.3438 0.07966 0.07767 -0.0275 1.0000 0.0218
-7.000 -0.3379 0.07528 0.07331 -0.0352 0.9983 0.0230
-6.750 -0.3019 0.06849 0.06645 -0.0473 0.9934 0.0232
-6.500 -0.2686 0.06159 0.05946 -0.0572 0.9878 0.0232
-6.000 -0.2210 0.05138 0.04914 -0.0675 0.9746 0.0248
-5.750 -0.1924 0.04792 0.04559 -0.0716 0.9650 0.0261
-5.500 -0.1538 0.04281 0.04022 -0.0773 0.9531 0.0301
-5.250 -0.1264 0.03723 0.03426 -0.0801 0.9389 0.0305
-5.000 -0.1121 0.02963 0.02634 -0.0822 0.9234 0.0321
-4.750 -0.0909 0.02862 0.02525 -0.0817 0.9060 0.0332
-4.500 -0.0680 0.02695 0.02339 -0.0814 0.8870 0.0352
-4.250 -0.0383 0.02673 0.02273 -0.0805 0.8663 0.0405
-4.000 -0.0182 0.02094 0.01650 -0.0813 0.8451 0.0435
-3.750 0.0074 0.00558 0.00069 -0.0772 0.7860 0.0384
-3.500 0.0367 0.01844 0.01317 -0.0799 0.7997 0.0405
-3.000 0.0899 0.01368 0.00759 -0.0794 0.7634 0.0388
-2.750 0.1175 0.01298 0.00665 -0.0792 0.7477 0.0394
-2.500 0.1455 0.01305 0.00656 -0.0790 0.7336 0.0406
-2.250 0.1730 0.01191 0.00522 -0.0788 0.7213 0.0411
-2.000 0.2005 0.01113 0.00431 -0.0786 0.7087 0.0417
-1.750 0.2281 0.01056 0.00365 -0.0785 0.6969 0.0424
-1.500 0.2558 0.01014 0.00316 -0.0783 0.6857 0.0439
-1.250 0.2836 0.00987 0.00282 -0.0783 0.6755 0.0457
-1.000 0.3117 0.00965 0.00255 -0.0782 0.6652 0.0470
-0.750 0.3398 0.00947 0.00232 -0.0781 0.6551 0.0487
-0.500 0.3679 0.00936 0.00213 -0.0781 0.6452 0.0506
-0.250 0.3960 0.00928 0.00198 -0.0780 0.6347 0.0524
0.000 0.4244 0.00916 0.00184 -0.0780 0.6246 0.0586
0.250 0.4523 0.00892 0.00182 -0.0781 0.6154 0.1327
0.500 0.4802 0.00870 0.00183 -0.0782 0.6058 0.2239
0.750 0.5060 0.00679 0.00191 -0.0780 0.5966 1.0000
1.000 0.5339 0.00689 0.00190 -0.0779 0.5871 1.0000
1.250 0.5618 0.00698 0.00190 -0.0779 0.5765 1.0000
1.500 0.5898 0.00706 0.00191 -0.0779 0.5655 1.0000
1.750 0.6176 0.00717 0.00193 -0.0778 0.5539 1.0000
2.000 0.6453 0.00728 0.00197 -0.0777 0.5415 1.0000
2.250 0.6730 0.00740 0.00201 -0.0777 0.5294 1.0000
2.500 0.7006 0.00752 0.00207 -0.0776 0.5166 1.0000
2.750 0.7282 0.00765 0.00214 -0.0776 0.5030 1.0000
3.000 0.7557 0.00780 0.00223 -0.0775 0.4889 1.0000
3.250 0.7830 0.00796 0.00232 -0.0774 0.4748 1.0000
3.500 0.8103 0.00812 0.00243 -0.0773 0.4610 1.0000
3.750 0.8376 0.00830 0.00256 -0.0773 0.4483 1.0000
4.000 0.8647 0.00849 0.00270 -0.0772 0.4341 1.0000
4.250 0.8916 0.00869 0.00285 -0.0771 0.4194 1.0000
4.500 0.9186 0.00889 0.00301 -0.0770 0.4075 1.0000
4.750 0.9454 0.00910 0.00320 -0.0769 0.3951 1.0000
5.000 0.9720 0.00932 0.00338 -0.0767 0.3790 1.0000
5.250 0.9982 0.00960 0.00357 -0.0766 0.3592 1.0000
5.500 1.0243 0.00988 0.00380 -0.0764 0.3416 1.0000
5.750 1.0504 0.01016 0.00403 -0.0762 0.3209 1.0000
6.000 1.0758 0.01051 0.00430 -0.0759 0.2975 1.0000
6.250 1.1006 0.01093 0.00460 -0.0756 0.2653 1.0000
6.500 1.1223 0.01173 0.00508 -0.0750 0.2069 1.0000
6.750 1.1445 0.01246 0.00561 -0.0744 0.1770 1.0000
7.000 1.1677 0.01304 0.00610 -0.0739 0.1594 1.0000
7.250 1.1916 0.01351 0.00653 -0.0734 0.1393 1.0000
7.500 1.2071 0.01498 0.00749 -0.0720 0.0607 1.0000
7.750 1.2232 0.01633 0.00858 -0.0705 0.0213 1.0000
8.000 1.2445 0.01703 0.00935 -0.0696 0.0187 1.0000
8.250 1.2646 0.01784 0.01026 -0.0684 0.0169 1.0000
8.500 1.2846 0.01859 0.01112 -0.0674 0.0162 1.0000
8.750 1.3035 0.01940 0.01204 -0.0662 0.0155 1.0000
9.000 1.3208 0.02031 0.01304 -0.0648 0.0146 1.0000
9.250 1.3361 0.02133 0.01414 -0.0632 0.0138 1.0000
9.500 1.3476 0.02256 0.01547 -0.0611 0.0132 1.0000
9.750 1.3540 0.02405 0.01705 -0.0583 0.0127 1.0000
10.000 1.3521 0.02580 0.01891 -0.0545 0.0124 1.0000
10.250 1.3475 0.02796 0.02119 -0.0509 0.0121 1.0000
10.500 1.3536 0.02947 0.02280 -0.0488 0.0120 1.0000
10.750 1.3607 0.03097 0.02441 -0.0470 0.0118 1.0000
11.000 1.3662 0.03272 0.02626 -0.0454 0.0116 1.0000
11.250 1.3711 0.03464 0.02827 -0.0438 0.0114 1.0000
11.500 1.3755 0.03670 0.03044 -0.0424 0.0113 1.0000
11.750 1.3801 0.03881 0.03265 -0.0411 0.0111 1.0000
12.000 1.3849 0.04097 0.03491 -0.0401 0.0108 1.0000
12.250 1.3893 0.04321 0.03725 -0.0392 0.0105 1.0000
12.500 1.3933 0.04553 0.03966 -0.0384 0.0102 1.0000
12.750 1.3968 0.04796 0.04221 -0.0376 0.0100 1.0000
13.000 1.3998 0.05049 0.04484 -0.0367 0.0098 1.0000
13.250 1.4024 0.05313 0.04758 -0.0359 0.0097 1.0000
13.500 1.4042 0.05591 0.05048 -0.0352 0.0096 1.0000
13.750 1.4052 0.05881 0.05350 -0.0346 0.0095 1.0000
14.000 1.4045 0.06199 0.05682 -0.0341 0.0095 1.0000
14.250 1.4011 0.06560 0.06060 -0.0340 0.0095 1.0000
14.500 1.3960 0.06942 0.06459 -0.0340 0.0095 1.0000
14.750 1.3868 0.07396 0.06933 -0.0346 0.0096 1.0000
15.000 1.3705 0.07978 0.07544 -0.0359 0.0098 1.0000
15.250 1.3541 0.08582 0.08173 -0.0375 0.0100 1.0000
15.500 1.3359 0.09249 0.08864 -0.0397 0.0103 1.0000
15.750 1.3183 0.09927 0.09563 -0.0423 0.0106 1.0000
16.000 1.3001 0.10642 0.10297 -0.0454 0.0109 1.0000
16.250 1.2820 0.11387 0.11060 -0.0490 0.0112 1.0000
16.500 1.2623 0.12189 0.11878 -0.0529 0.0115 1.0000
17.000 1.0217 0.12104 0.11819 -0.0366 0.0108 1.0000
17.250 1.0008 0.12688 0.12417 -0.0399 0.0110 1.0000
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Polar data table (+)
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