GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il) Reynolds number: 50,000 Max Cl/Cd: 38.29 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe134-il-50000-n5.txt Download as CSV file: xf-goe134-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 134 (MVA H.12) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3716 0.10617 0.09937 -0.0231 1.0000 0.1043
-8.000 -0.3770 0.10404 0.09734 -0.0247 1.0000 0.1086
-7.750 -0.3917 0.10282 0.09628 -0.0290 1.0000 0.1105
-7.500 -0.3839 0.09819 0.09172 -0.0276 1.0000 0.1129
-7.250 -0.3742 0.09458 0.08814 -0.0255 1.0000 0.1179
-7.000 -0.3764 0.09201 0.08565 -0.0278 1.0000 0.1237
-6.750 -0.3826 0.08945 0.08316 -0.0334 1.0000 0.1272
-6.500 -0.3713 0.08547 0.07926 -0.0284 1.0000 0.1326
-6.000 -0.3650 0.07942 0.07331 -0.0296 1.0000 0.1487
-5.750 -0.3621 0.07641 0.07032 -0.0319 1.0000 0.1601
-5.500 -0.3566 0.07369 0.06756 -0.0334 1.0000 0.1743
-5.250 -0.3490 0.07059 0.06456 -0.0303 1.0000 0.1828
-5.000 -0.3421 0.06766 0.06165 -0.0301 1.0000 0.1965
-4.750 -0.3346 0.06495 0.05895 -0.0298 1.0000 0.2139
-4.500 -0.3284 0.06235 0.05639 -0.0291 1.0000 0.2392
-4.000 -0.2512 0.05085 0.04370 -0.0434 1.0000 0.1041
-3.750 -0.2192 0.04699 0.03900 -0.0455 1.0000 0.0799
-3.500 -0.1949 0.04383 0.03573 -0.0467 0.9976 0.0767
-3.250 -0.1514 0.04054 0.03195 -0.0511 0.9897 0.0753
-3.000 -0.1078 0.03779 0.02868 -0.0550 0.9814 0.0755
-2.750 -0.0641 0.03524 0.02561 -0.0585 0.9730 0.0732
-2.500 -0.0206 0.03310 0.02296 -0.0617 0.9642 0.0717
-2.250 0.0198 0.03144 0.02090 -0.0643 0.9536 0.0730
-2.000 0.0603 0.03004 0.01915 -0.0667 0.9430 0.0752
-1.750 0.1046 0.02863 0.01741 -0.0696 0.9345 0.0752
-1.500 0.1429 0.02750 0.01603 -0.0713 0.9222 0.0754
-1.250 0.1811 0.02651 0.01485 -0.0728 0.9101 0.0760
-1.000 0.2196 0.02568 0.01381 -0.0743 0.8979 0.0775
-0.750 0.2570 0.02501 0.01296 -0.0757 0.8849 0.0810
-0.500 0.2925 0.02419 0.01210 -0.0769 0.8711 0.0849
-0.250 0.3269 0.02361 0.01139 -0.0777 0.8560 0.0878
0.000 0.3604 0.02312 0.01077 -0.0784 0.8403 0.0916
0.250 0.3934 0.02269 0.01023 -0.0788 0.8242 0.0972
0.500 0.4259 0.02225 0.00975 -0.0793 0.8079 0.1088
0.750 0.4541 0.01945 0.00948 -0.0786 0.7925 1.0000
1.000 0.4850 0.01949 0.00914 -0.0784 0.7758 1.0000
1.250 0.5149 0.01957 0.00889 -0.0782 0.7592 1.0000
1.500 0.5440 0.01968 0.00873 -0.0778 0.7426 1.0000
1.750 0.5723 0.01985 0.00866 -0.0774 0.7260 1.0000
2.000 0.5991 0.02008 0.00870 -0.0769 0.7084 1.0000
2.250 0.6255 0.02035 0.00881 -0.0763 0.6908 1.0000
2.500 0.6520 0.02064 0.00897 -0.0759 0.6734 1.0000
2.750 0.6783 0.02094 0.00916 -0.0754 0.6562 1.0000
3.000 0.7045 0.02125 0.00937 -0.0749 0.6393 1.0000
3.250 0.7305 0.02157 0.00960 -0.0744 0.6227 1.0000
3.500 0.7565 0.02189 0.00987 -0.0739 0.6064 1.0000
3.750 0.7823 0.02223 0.01014 -0.0734 0.5905 1.0000
4.000 0.8081 0.02259 0.01046 -0.0729 0.5750 1.0000
4.250 0.8338 0.02297 0.01082 -0.0724 0.5597 1.0000
4.500 0.8593 0.02337 0.01121 -0.0720 0.5449 1.0000
4.750 0.8847 0.02382 0.01166 -0.0715 0.5305 1.0000
5.000 0.9099 0.02429 0.01217 -0.0711 0.5164 1.0000
5.250 0.9351 0.02479 0.01271 -0.0707 0.5030 1.0000
5.500 0.9601 0.02533 0.01329 -0.0702 0.4902 1.0000
5.750 0.9853 0.02587 0.01390 -0.0698 0.4781 1.0000
6.000 1.0108 0.02640 0.01445 -0.0694 0.4669 1.0000
6.250 1.0348 0.02705 0.01524 -0.0690 0.4548 1.0000
6.500 1.0587 0.02773 0.01604 -0.0685 0.4433 1.0000
6.750 1.0830 0.02839 0.01684 -0.0680 0.4326 1.0000
7.000 1.1078 0.02899 0.01752 -0.0675 0.4223 1.0000
7.250 1.1297 0.02971 0.01841 -0.0667 0.4097 1.0000
7.500 1.1513 0.03036 0.01924 -0.0658 0.3963 1.0000
7.750 1.1724 0.03099 0.02001 -0.0648 0.3826 1.0000
8.000 1.1931 0.03166 0.02082 -0.0638 0.3693 1.0000
8.250 1.2138 0.03236 0.02167 -0.0628 0.3567 1.0000
8.500 1.2343 0.03305 0.02255 -0.0617 0.3442 1.0000
8.750 1.2539 0.03375 0.02339 -0.0605 0.3311 1.0000
9.000 1.2719 0.03449 0.02430 -0.0592 0.3172 1.0000
9.250 1.2878 0.03532 0.02534 -0.0576 0.3027 1.0000
9.500 1.3024 0.03621 0.02644 -0.0558 0.2880 1.0000
9.750 1.3157 0.03719 0.02768 -0.0540 0.2734 1.0000
10.000 1.3270 0.03823 0.02893 -0.0519 0.2587 1.0000
10.250 1.3351 0.03928 0.03013 -0.0495 0.2428 1.0000
10.500 1.3374 0.04053 0.03156 -0.0467 0.2255 1.0000
10.750 1.3351 0.04197 0.03316 -0.0435 0.2077 1.0000
11.000 1.3292 0.04363 0.03493 -0.0401 0.1916 1.0000
11.250 1.3241 0.04568 0.03708 -0.0375 0.1765 1.0000
11.500 1.3183 0.04811 0.03963 -0.0355 0.1623 1.0000
11.750 1.3097 0.05106 0.04263 -0.0341 0.1478 1.0000
12.000 1.2990 0.05461 0.04619 -0.0335 0.1338 1.0000
12.250 1.2878 0.05868 0.05029 -0.0334 0.1215 1.0000
12.500 1.2762 0.06313 0.05480 -0.0339 0.1110 1.0000
12.750 1.2629 0.06797 0.05962 -0.0346 0.1027 1.0000
13.000 1.2509 0.07306 0.06490 -0.0357 0.0931 1.0000
13.250 1.2376 0.07841 0.07033 -0.0370 0.0851 1.0000
13.500 1.2240 0.08390 0.07587 -0.0385 0.0784 1.0000
13.750 1.2117 0.08941 0.08148 -0.0400 0.0715 1.0000
14.000 1.1996 0.09484 0.08692 -0.0417 0.0665 1.0000
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Polar data table (+)
Polar graphs
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