GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 100,000 Max Cl/Cd: 53.83 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe133-il-100000.txt Download as CSV file: xf-goe133-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 133 (MVA H.11) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3641 0.09184 0.08710 -0.0206 1.0000 0.0706
-7.250 -0.3625 0.08913 0.08446 -0.0223 1.0000 0.0727
-7.000 -0.3604 0.08663 0.08203 -0.0272 1.0000 0.0751
-6.750 -0.3557 0.08492 0.08028 -0.0376 1.0000 0.0765
-6.500 -0.3512 0.08030 0.07571 -0.0380 1.0000 0.0773
-6.250 -0.3471 0.07632 0.07183 -0.0325 1.0000 0.0789
-6.000 -0.3413 0.07347 0.06902 -0.0306 1.0000 0.0812
-5.750 -0.3345 0.07065 0.06622 -0.0310 1.0000 0.0843
-5.500 -0.3121 0.06896 0.06414 -0.0420 1.0000 0.0910
-5.250 -0.3083 0.06386 0.05921 -0.0397 1.0000 0.0924
-5.000 -0.3042 0.06099 0.05648 -0.0361 1.0000 0.0953
-4.750 -0.2774 0.05918 0.05421 -0.0428 1.0000 0.1063
-4.500 -0.2742 0.05490 0.05020 -0.0395 1.0000 0.1086
-4.250 -0.2630 0.05239 0.04771 -0.0384 1.0000 0.1138
-4.000 -0.2411 0.04927 0.04436 -0.0413 1.0000 0.1234
-3.750 -0.2236 0.04726 0.04225 -0.0415 1.0000 0.1339
-3.500 -0.2078 0.04414 0.03912 -0.0417 1.0000 0.1410
-3.250 -0.1888 0.04183 0.03670 -0.0424 1.0000 0.1559
-3.000 -0.1699 0.03984 0.03464 -0.0428 1.0000 0.1751
-2.750 -0.1372 0.03715 0.03183 -0.0458 0.9968 0.2023
-2.250 -0.0087 0.02840 0.02130 -0.0588 0.9852 0.1244
-2.000 0.0434 0.02552 0.01782 -0.0628 0.9777 0.1137
-1.750 0.0972 0.02341 0.01518 -0.0672 0.9709 0.1139
-1.500 0.1452 0.02202 0.01340 -0.0706 0.9600 0.1185
-1.250 0.1926 0.02070 0.01195 -0.0742 0.9491 0.1266
-1.000 0.2447 0.01959 0.01070 -0.0783 0.9403 0.1338
-0.750 0.2916 0.01855 0.00973 -0.0816 0.9282 0.1470
-0.500 0.3337 0.01756 0.00886 -0.0837 0.9143 0.1603
-0.250 0.3729 0.01665 0.00809 -0.0852 0.8993 0.1881
0.000 0.4098 0.01373 0.00729 -0.0854 0.8852 1.0000
0.250 0.4453 0.01352 0.00675 -0.0857 0.8674 1.0000
0.500 0.4739 0.01343 0.00647 -0.0850 0.8443 1.0000
0.750 0.5035 0.01328 0.00612 -0.0842 0.8235 1.0000
1.000 0.5296 0.01325 0.00591 -0.0829 0.7983 1.0000
1.250 0.5557 0.01324 0.00571 -0.0816 0.7742 1.0000
1.500 0.5814 0.01330 0.00555 -0.0802 0.7499 1.0000
1.750 0.6066 0.01346 0.00554 -0.0791 0.7255 1.0000
2.000 0.6326 0.01366 0.00556 -0.0782 0.7052 1.0000
2.250 0.6587 0.01391 0.00568 -0.0775 0.6869 1.0000
2.500 0.6846 0.01419 0.00586 -0.0768 0.6686 1.0000
2.750 0.7107 0.01446 0.00605 -0.0762 0.6515 1.0000
3.000 0.7367 0.01474 0.00625 -0.0756 0.6351 1.0000
3.250 0.7628 0.01503 0.00647 -0.0750 0.6193 1.0000
3.500 0.7888 0.01533 0.00671 -0.0744 0.6036 1.0000
3.750 0.8147 0.01565 0.00699 -0.0738 0.5877 1.0000
4.000 0.8404 0.01597 0.00725 -0.0732 0.5714 1.0000
4.250 0.8660 0.01632 0.00753 -0.0725 0.5546 1.0000
4.500 0.8910 0.01669 0.00791 -0.0718 0.5357 1.0000
4.750 0.9158 0.01709 0.00828 -0.0711 0.5158 1.0000
5.000 0.9407 0.01751 0.00863 -0.0703 0.4957 1.0000
5.250 0.9647 0.01794 0.00906 -0.0694 0.4725 1.0000
5.500 0.9889 0.01837 0.00942 -0.0685 0.4498 1.0000
5.750 1.0122 0.01881 0.00987 -0.0676 0.4255 1.0000
6.000 1.0363 0.01928 0.01026 -0.0668 0.4053 1.0000
6.250 1.0599 0.01975 0.01076 -0.0660 0.3856 1.0000
6.500 1.0834 0.02018 0.01124 -0.0653 0.3672 1.0000
6.750 1.1069 0.02061 0.01170 -0.0645 0.3507 1.0000
7.000 1.1305 0.02109 0.01223 -0.0638 0.3360 1.0000
7.250 1.1536 0.02156 0.01277 -0.0630 0.3212 1.0000
7.500 1.1758 0.02198 0.01323 -0.0621 0.3050 1.0000
7.750 1.1976 0.02249 0.01378 -0.0612 0.2892 1.0000
8.000 1.2183 0.02307 0.01442 -0.0601 0.2712 1.0000
8.250 1.2375 0.02374 0.01520 -0.0589 0.2500 1.0000
8.500 1.2539 0.02464 0.01611 -0.0573 0.2231 1.0000
8.750 1.2670 0.02587 0.01725 -0.0553 0.1903 1.0000
9.000 1.2801 0.02729 0.01860 -0.0533 0.1623 1.0000
9.250 1.2944 0.02861 0.01985 -0.0515 0.1433 1.0000
9.500 1.3091 0.02978 0.02110 -0.0498 0.1276 1.0000
9.750 1.3226 0.03102 0.02238 -0.0480 0.1149 1.0000
10.000 1.3347 0.03252 0.02385 -0.0462 0.1044 1.0000
10.250 1.3465 0.03446 0.02562 -0.0445 0.0948 1.0000
10.500 1.3579 0.03644 0.02777 -0.0426 0.0862 1.0000
10.750 1.3719 0.03926 0.03068 -0.0411 0.0786 1.0000
11.000 1.3921 0.04306 0.03431 -0.0409 0.0700 1.0000
11.250 1.3959 0.04516 0.03691 -0.0380 0.0663 1.0000
11.500 1.4038 0.04782 0.03981 -0.0361 0.0622 1.0000
11.750 1.4201 0.05229 0.04423 -0.0359 0.0576 1.0000
12.000 1.4116 0.05449 0.04689 -0.0323 0.0561 1.0000
12.250 1.4016 0.05730 0.05007 -0.0290 0.0548 1.0000
12.500 1.3902 0.06060 0.05371 -0.0264 0.0539 1.0000
12.750 1.3761 0.06427 0.05769 -0.0244 0.0533 1.0000
13.000 1.3592 0.06839 0.06210 -0.0233 0.0529 1.0000
13.250 1.3395 0.07307 0.06707 -0.0231 0.0528 1.0000
13.500 1.3168 0.07847 0.07276 -0.0240 0.0528 1.0000
13.750 1.2913 0.08477 0.07931 -0.0263 0.0532 1.0000
14.000 1.2632 0.09206 0.08685 -0.0298 0.0537 1.0000
14.250 1.2335 0.10041 0.09540 -0.0346 0.0545 1.0000
14.500 1.2030 0.10976 0.10492 -0.0404 0.0554 1.0000
14.750 1.1728 0.11995 0.11523 -0.0468 0.0565 1.0000
15.000 1.1453 0.13066 0.12600 -0.0533 0.0574 1.0000
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Polar data table (+)
Polar graphs
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