GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.27 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe144-il-1000000.txt Download as CSV file: xf-goe144-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 144 (MVA H.21) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2756 0.10465 0.10312 -0.0256 1.0000 0.0121
-10.000 -0.2738 0.10142 0.09989 -0.0258 1.0000 0.0128
-8.250 -0.4519 0.02002 0.01705 -0.0951 0.9843 0.0099
-8.000 -0.4241 0.01836 0.01517 -0.0962 0.9816 0.0102
-7.750 -0.3994 0.01540 0.01177 -0.0972 0.9775 0.0110
-7.500 -0.3679 0.01478 0.01108 -0.0983 0.9753 0.0117
-7.250 -0.3359 0.01411 0.01031 -0.0995 0.9736 0.0123
-7.000 -0.3032 0.01342 0.00951 -0.1007 0.9722 0.0130
-6.750 -0.2719 0.01280 0.00877 -0.1015 0.9699 0.0138
-6.500 -0.2444 0.01240 0.00828 -0.1014 0.9648 0.0142
-6.250 -0.2139 0.01115 0.00687 -0.1023 0.9615 0.0157
-6.000 -0.1797 0.01086 0.00653 -0.1036 0.9589 0.0168
-5.750 -0.1489 0.01062 0.00625 -0.1041 0.9543 0.0181
-5.500 -0.1167 0.01055 0.00614 -0.1049 0.9493 0.0190
-5.250 -0.0841 0.00946 0.00490 -0.1061 0.9447 0.0211
-5.000 -0.0535 0.00916 0.00454 -0.1066 0.9378 0.0226
-4.750 -0.0209 0.00888 0.00419 -0.1075 0.9311 0.0243
-4.500 0.0087 0.00876 0.00402 -0.1077 0.9228 0.0255
-4.250 0.0377 0.00821 0.00332 -0.1078 0.9147 0.0273
-4.000 0.0646 0.00781 0.00283 -0.1074 0.9056 0.0295
-3.750 0.0919 0.00758 0.00253 -0.1072 0.8964 0.0315
-3.500 0.1192 0.00740 0.00227 -0.1068 0.8863 0.0330
-3.250 0.1456 0.00723 0.00203 -0.1063 0.8748 0.0341
-3.000 0.1720 0.00708 0.00180 -0.1057 0.8609 0.0356
-2.750 0.1979 0.00690 0.00156 -0.1050 0.8415 0.0396
-2.500 0.2222 0.00679 0.00138 -0.1040 0.8015 0.0486
-2.250 0.2440 0.00695 0.00133 -0.1024 0.7414 0.0665
-2.000 0.2679 0.00708 0.00130 -0.1014 0.7060 0.0734
-1.750 0.2931 0.00718 0.00128 -0.1007 0.6806 0.0778
-1.500 0.3189 0.00726 0.00125 -0.1001 0.6591 0.0801
-1.250 0.3448 0.00730 0.00119 -0.0995 0.6403 0.0826
-1.000 0.3709 0.00730 0.00114 -0.0990 0.6214 0.0866
-0.750 0.3970 0.00732 0.00110 -0.0985 0.6023 0.0894
-0.500 0.4232 0.00736 0.00106 -0.0980 0.5852 0.0918
-0.250 0.4497 0.00738 0.00104 -0.0976 0.5718 0.0952
0.000 0.4762 0.00739 0.00103 -0.0972 0.5585 0.1027
0.250 0.5024 0.00742 0.00107 -0.0968 0.5432 0.1193
0.500 0.5290 0.00748 0.00111 -0.0964 0.5303 0.1349
0.750 0.5557 0.00753 0.00115 -0.0961 0.5200 0.1466
1.000 0.5823 0.00758 0.00119 -0.0957 0.5096 0.1542
1.250 0.6091 0.00763 0.00123 -0.0954 0.4989 0.1597
1.500 0.6357 0.00770 0.00126 -0.0950 0.4871 0.1636
1.750 0.6622 0.00776 0.00130 -0.0947 0.4763 0.1686
2.000 0.6888 0.00782 0.00134 -0.0943 0.4663 0.1729
2.250 0.7155 0.00788 0.00140 -0.0940 0.4557 0.1767
2.500 0.7419 0.00794 0.00146 -0.0936 0.4445 0.1834
2.750 0.7682 0.00802 0.00153 -0.0932 0.4331 0.1910
3.000 0.7943 0.00809 0.00162 -0.0929 0.4206 0.2098
3.250 0.8205 0.00812 0.00174 -0.0925 0.4090 0.2538
3.500 0.8465 0.00814 0.00185 -0.0921 0.3969 0.3088
3.750 0.8819 0.00704 0.00212 -0.0943 0.3747 1.0000
4.000 0.9059 0.00733 0.00226 -0.0935 0.3415 1.0000
4.250 0.9302 0.00761 0.00241 -0.0928 0.3149 1.0000
4.500 0.9536 0.00797 0.00261 -0.0920 0.2817 1.0000
4.750 0.9765 0.00839 0.00285 -0.0911 0.2486 1.0000
5.000 0.9996 0.00879 0.00310 -0.0902 0.2196 1.0000
5.250 1.0230 0.00916 0.00335 -0.0894 0.1941 1.0000
5.500 1.0425 0.00993 0.00377 -0.0881 0.1302 1.0000
5.750 1.0622 0.01068 0.00427 -0.0867 0.0889 1.0000
6.000 1.0790 0.01172 0.00495 -0.0849 0.0254 1.0000
6.250 1.1016 0.01218 0.00542 -0.0838 0.0170 1.0000
6.500 1.1253 0.01252 0.00580 -0.0830 0.0157 1.0000
6.750 1.1481 0.01293 0.00625 -0.0821 0.0142 1.0000
7.000 1.1694 0.01349 0.00687 -0.0809 0.0125 1.0000
7.250 1.1905 0.01405 0.00751 -0.0796 0.0117 1.0000
7.500 1.2126 0.01448 0.00799 -0.0786 0.0112 1.0000
7.750 1.2338 0.01499 0.00855 -0.0775 0.0107 1.0000
8.000 1.2543 0.01554 0.00915 -0.0762 0.0101 1.0000
8.250 1.2741 0.01612 0.00977 -0.0749 0.0095 1.0000
8.500 1.2921 0.01683 0.01053 -0.0733 0.0090 1.0000
8.750 1.2975 0.01852 0.01238 -0.0696 0.0083 1.0000
9.000 1.3170 0.01899 0.01290 -0.0683 0.0081 1.0000
9.250 1.3337 0.01965 0.01361 -0.0665 0.0078 1.0000
9.500 1.3483 0.02042 0.01444 -0.0644 0.0076 1.0000
9.750 1.3598 0.02124 0.01534 -0.0619 0.0073 1.0000
10.000 1.3673 0.02216 0.01633 -0.0586 0.0071 1.0000
10.250 1.3744 0.02312 0.01735 -0.0554 0.0070 1.0000
10.500 1.3835 0.02398 0.01828 -0.0527 0.0067 1.0000
10.750 1.3894 0.02509 0.01947 -0.0497 0.0066 1.0000
11.000 1.3938 0.02638 0.02083 -0.0468 0.0065 1.0000
11.250 1.4033 0.02726 0.02176 -0.0448 0.0062 1.0000
11.500 1.4053 0.02885 0.02344 -0.0421 0.0061 1.0000
11.750 1.4076 0.03053 0.02519 -0.0397 0.0060 1.0000
12.000 1.4049 0.03282 0.02754 -0.0372 0.0057 1.0000
12.250 1.3999 0.03606 0.03090 -0.0347 0.0056 1.0000
12.500 1.4004 0.03851 0.03349 -0.0330 0.0054 1.0000
12.750 1.4039 0.04020 0.03529 -0.0319 0.0054 1.0000
13.000 1.4074 0.04207 0.03728 -0.0311 0.0052 1.0000
13.250 1.4065 0.04490 0.04025 -0.0302 0.0052 1.0000
13.500 1.4065 0.04760 0.04307 -0.0298 0.0051 1.0000
13.750 1.4041 0.05079 0.04640 -0.0295 0.0050 1.0000
14.000 1.4006 0.05422 0.04998 -0.0294 0.0049 1.0000
14.250 1.3949 0.05812 0.05402 -0.0296 0.0049 1.0000
14.500 1.3874 0.06239 0.05845 -0.0302 0.0049 1.0000
14.750 1.3800 0.06674 0.06295 -0.0312 0.0048 1.0000
15.000 1.3674 0.07213 0.06852 -0.0325 0.0048 1.0000
15.250 1.3558 0.07754 0.07409 -0.0344 0.0048 1.0000
15.500 1.3447 0.08305 0.07975 -0.0367 0.0048 1.0000
15.750 1.3290 0.08964 0.08651 -0.0396 0.0049 1.0000
16.000 1.3150 0.09620 0.09323 -0.0428 0.0048 1.0000
16.250 1.2998 0.10334 0.10052 -0.0466 0.0048 1.0000
16.500 1.2855 0.11052 0.10784 -0.0506 0.0048 1.0000
16.750 1.2693 0.11849 0.11596 -0.0552 0.0048 1.0000
17.000 1.2527 0.12684 0.12445 -0.0602 0.0049 1.0000
17.250 1.2343 0.13602 0.13377 -0.0659 0.0050 1.0000
17.500 1.2172 0.14525 0.14314 -0.0717 0.0050 1.0000
17.750 1.2030 0.15419 0.15220 -0.0775 0.0050 1.0000
18.000 1.1856 0.16426 0.16239 -0.0839 0.0051 1.0000
18.250 1.1673 0.17513 0.17336 -0.0909 0.0052 1.0000
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Polar data table (+)
Polar graphs
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