GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Reynolds number: 50,000 Max Cl/Cd: 39.9 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe165-il-50000-n5.txt Download as CSV file: xf-goe165-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 165 (MVA MK.11) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2926 0.10944 0.10302 -0.0369 1.0000 0.0515
-8.500 -0.2897 0.10637 0.10003 -0.0363 1.0000 0.0490
-8.000 -0.3124 0.09863 0.09257 -0.0387 1.0000 0.0426
-7.750 -0.3103 0.09627 0.09029 -0.0368 1.0000 0.0419
-7.500 -0.3143 0.09389 0.08802 -0.0354 1.0000 0.0413
-7.250 -0.3212 0.09149 0.08575 -0.0340 1.0000 0.0407
-7.000 -0.3270 0.08872 0.08310 -0.0334 1.0000 0.0400
-6.750 -0.3327 0.08570 0.08022 -0.0334 1.0000 0.0394
-6.500 -0.3383 0.08239 0.07703 -0.0341 1.0000 0.0388
-6.250 -0.3431 0.07861 0.07337 -0.0356 1.0000 0.0382
-6.000 -0.3460 0.07383 0.06867 -0.0391 1.0000 0.0373
-5.750 -0.2953 0.05544 0.04946 -0.0740 0.9930 0.0342
-5.500 -0.2482 0.04885 0.04241 -0.0864 0.9870 0.0349
-5.250 -0.2046 0.04436 0.03752 -0.0946 0.9803 0.0365
-5.000 -0.1577 0.04024 0.03279 -0.1022 0.9742 0.0377
-4.750 -0.1128 0.03713 0.02908 -0.1073 0.9685 0.0384
-4.500 -0.0743 0.03499 0.02653 -0.1101 0.9607 0.0395
-4.250 -0.0355 0.03340 0.02459 -0.1122 0.9540 0.0412
-4.000 -0.0005 0.03205 0.02312 -0.1140 0.9456 0.0452
-3.750 0.0366 0.03095 0.02186 -0.1162 0.9375 0.0506
-3.500 0.0803 0.02963 0.02037 -0.1199 0.9296 0.0565
-3.250 0.1295 0.02768 0.01846 -0.1258 0.9195 0.0756
-3.000 0.1748 0.02720 0.01912 -0.1293 0.9074 0.3178
-2.750 0.2014 0.02959 0.02136 -0.1260 0.8909 0.3874
-2.500 0.2372 0.02981 0.02127 -0.1262 0.8764 0.4126
-2.250 0.2730 0.02955 0.02076 -0.1267 0.8628 0.4292
-2.000 0.3131 0.02897 0.01985 -0.1287 0.8505 0.4419
-1.750 0.3515 0.02834 0.01897 -0.1305 0.8390 0.4483
-1.500 0.3890 0.02780 0.01809 -0.1327 0.8260 0.4559
-1.250 0.4221 0.02735 0.01748 -0.1334 0.8129 0.4615
-1.000 0.4591 0.02691 0.01677 -0.1352 0.7995 0.4696
-0.750 0.4933 0.02649 0.01619 -0.1361 0.7860 0.4755
-0.500 0.5292 0.02612 0.01561 -0.1375 0.7718 0.4833
-0.250 0.5631 0.02577 0.01510 -0.1383 0.7568 0.4896
0.000 0.5971 0.02551 0.01465 -0.1392 0.7409 0.4973
0.250 0.6299 0.02529 0.01428 -0.1398 0.7244 0.5038
0.500 0.6622 0.02515 0.01397 -0.1404 0.7072 0.5109
0.750 0.6939 0.02507 0.01370 -0.1408 0.6894 0.5173
1.000 0.7230 0.02506 0.01355 -0.1408 0.6705 0.5234
1.250 0.7514 0.02515 0.01350 -0.1408 0.6503 0.5298
1.500 0.7787 0.02519 0.01344 -0.1405 0.6304 0.5348
1.750 0.8063 0.02531 0.01343 -0.1403 0.6103 0.5407
2.000 0.8315 0.02549 0.01354 -0.1398 0.5884 0.5460
2.250 0.8571 0.02564 0.01362 -0.1393 0.5682 0.5509
2.500 0.8832 0.02585 0.01376 -0.1389 0.5492 0.5562
2.750 0.9086 0.02608 0.01395 -0.1386 0.5311 0.5612
3.000 0.9343 0.02631 0.01413 -0.1382 0.5153 0.5665
3.250 0.9606 0.02659 0.01436 -0.1379 0.5013 0.5720
3.500 0.9870 0.02685 0.01456 -0.1377 0.4895 0.5768
3.750 1.0133 0.02717 0.01488 -0.1375 0.4785 0.5823
4.250 1.0674 0.02790 0.01563 -0.1373 0.4615 0.5945
4.500 1.0933 0.02839 0.01620 -0.1372 0.4530 0.6010
4.750 1.1209 0.02878 0.01664 -0.1372 0.4464 0.6074
5.000 1.1458 0.02934 0.01736 -0.1369 0.4389 0.6146
5.250 1.1727 0.02981 0.01794 -0.1368 0.4330 0.6229
5.500 1.1982 0.03041 0.01871 -0.1366 0.4271 0.6326
5.750 1.2226 0.03097 0.01952 -0.1362 0.4204 0.6434
6.000 1.2475 0.03148 0.02020 -0.1358 0.4134 0.6567
6.250 1.2689 0.03203 0.02105 -0.1349 0.4051 0.6756
6.500 1.2888 0.03230 0.02170 -0.1334 0.3977 0.7659
6.750 1.3093 0.03301 0.02259 -0.1324 0.3895 1.0000
7.000 1.3328 0.03379 0.02352 -0.1318 0.3822 1.0000
7.250 1.3530 0.03452 0.02436 -0.1307 0.3725 1.0000
7.500 1.3673 0.03499 0.02484 -0.1285 0.3566 1.0000
7.750 1.3788 0.03543 0.02527 -0.1258 0.3399 1.0000
8.000 1.3891 0.03614 0.02615 -0.1232 0.3267 1.0000
8.250 1.3993 0.03690 0.02708 -0.1207 0.3147 1.0000
8.500 1.4085 0.03767 0.02800 -0.1181 0.3028 1.0000
8.750 1.4119 0.03851 0.02898 -0.1147 0.2878 1.0000
9.000 1.4104 0.03953 0.03015 -0.1108 0.2713 1.0000
9.250 1.4123 0.04074 0.03164 -0.1077 0.2565 1.0000
9.500 1.4133 0.04220 0.03331 -0.1048 0.2398 1.0000
9.750 1.4146 0.04388 0.03521 -0.1023 0.2208 1.0000
10.000 1.4152 0.04583 0.03733 -0.1001 0.1948 1.0000
10.250 1.4068 0.04839 0.03967 -0.0976 0.1537 1.0000
10.500 1.3894 0.05236 0.04331 -0.0957 0.1251 1.0000
10.750 1.3761 0.05663 0.04756 -0.0947 0.0904 1.0000
11.250 1.3320 0.06859 0.05946 -0.0954 0.0607 1.0000
11.500 1.3123 0.07486 0.06584 -0.0965 0.0578 1.0000
11.750 1.2930 0.08134 0.07247 -0.0980 0.0555 1.0000
12.000 1.2741 0.08800 0.07927 -0.0997 0.0535 1.0000
12.250 1.2585 0.09430 0.08574 -0.1014 0.0504 1.0000
12.500 1.2450 0.10040 0.09204 -0.1032 0.0476 1.0000
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Polar data table (+)
Polar graphs
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