GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il) Reynolds number: 100,000 Max Cl/Cd: 59.79 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe155-il-100000.txt Download as CSV file: xf-goe155-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 155 (SSW D.1) 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 -0.3038 0.09531 0.09083 -0.0260 1.0000 0.0571
-7.250 -0.3074 0.09397 0.08959 -0.0267 1.0000 0.0589
-7.000 -0.3193 0.09379 0.08952 -0.0264 1.0000 0.0599
-6.750 -0.3323 0.09396 0.08977 -0.0265 1.0000 0.0604
-6.500 -0.3388 0.09404 0.08989 -0.0291 1.0000 0.0607
-6.250 -0.3387 0.09238 0.08825 -0.0315 1.0000 0.0611
-6.000 -0.3466 0.08707 0.08305 -0.0227 1.0000 0.0624
-5.750 -0.3483 0.08452 0.08054 -0.0199 1.0000 0.0640
-5.500 -0.3471 0.08228 0.07832 -0.0192 1.0000 0.0658
-5.250 -0.3408 0.07986 0.07590 -0.0204 0.9997 0.0682
-5.000 -0.2741 0.07557 0.07131 -0.0414 0.9927 0.0740
-4.750 -0.2642 0.07067 0.06648 -0.0389 0.9884 0.0760
-4.500 -0.2308 0.06677 0.06252 -0.0440 0.9837 0.0816
-4.250 -0.1889 0.06259 0.05816 -0.0532 0.9772 0.0890
-3.750 -0.1135 0.05519 0.05051 -0.0644 0.9651 0.1048
-3.500 -0.0632 0.05144 0.04653 -0.0725 0.9586 0.1167
-3.250 -0.0215 0.04842 0.04332 -0.0780 0.9508 0.1303
-3.000 0.0207 0.04527 0.04003 -0.0829 0.9448 0.1456
-2.750 0.0584 0.04265 0.03723 -0.0867 0.9381 0.1601
-2.500 0.0963 0.04010 0.03456 -0.0902 0.9319 0.1766
-2.250 0.1444 0.03741 0.03168 -0.0956 0.9283 0.2040
-1.250 0.3229 0.02912 0.02141 -0.1075 0.9019 0.1277
-1.000 0.3605 0.02663 0.01866 -0.1089 0.8954 0.1092
-0.750 0.3964 0.02525 0.01695 -0.1098 0.8877 0.1060
-0.500 0.4314 0.02414 0.01539 -0.1102 0.8801 0.1010
-0.250 0.4651 0.02315 0.01425 -0.1105 0.8722 0.0993
0.000 0.4940 0.02239 0.01341 -0.1102 0.8625 0.0991
0.250 0.5276 0.02153 0.01245 -0.1102 0.8555 0.1002
0.500 0.5533 0.02088 0.01191 -0.1092 0.8440 0.1037
0.750 0.5803 0.02034 0.01138 -0.1080 0.8325 0.1109
1.000 0.6084 0.01975 0.01078 -0.1067 0.8206 0.1285
1.250 0.6368 0.01874 0.01003 -0.1052 0.8091 0.2111
1.500 0.6660 0.01680 0.00937 -0.1041 0.7965 1.0000
1.750 0.6906 0.01673 0.00912 -0.1025 0.7830 1.0000
2.000 0.7154 0.01669 0.00896 -0.1012 0.7696 1.0000
2.250 0.7404 0.01665 0.00882 -0.0998 0.7559 1.0000
2.500 0.7654 0.01659 0.00867 -0.0985 0.7418 1.0000
2.750 0.7905 0.01655 0.00854 -0.0973 0.7271 1.0000
3.000 0.8158 0.01651 0.00844 -0.0960 0.7118 1.0000
3.250 0.8412 0.01650 0.00838 -0.0949 0.6960 1.0000
3.500 0.8667 0.01648 0.00829 -0.0938 0.6795 1.0000
3.750 0.8921 0.01648 0.00822 -0.0927 0.6621 1.0000
4.000 0.9170 0.01656 0.00830 -0.0918 0.6415 1.0000
4.250 0.9425 0.01659 0.00831 -0.0908 0.6220 1.0000
4.500 0.9678 0.01669 0.00836 -0.0899 0.6016 1.0000
4.750 0.9928 0.01687 0.00849 -0.0890 0.5798 1.0000
5.000 1.0180 0.01709 0.00864 -0.0882 0.5587 1.0000
5.250 1.0427 0.01744 0.00896 -0.0874 0.5360 1.0000
5.500 1.0675 0.01787 0.00930 -0.0866 0.5146 1.0000
5.750 1.0915 0.01835 0.00972 -0.0858 0.4915 1.0000
6.000 1.1150 0.01886 0.01016 -0.0849 0.4683 1.0000
6.250 1.1381 0.01936 0.01061 -0.0840 0.4456 1.0000
6.500 1.1602 0.01986 0.01112 -0.0830 0.4226 1.0000
6.750 1.1829 0.02036 0.01165 -0.0821 0.4032 1.0000
7.000 1.2037 0.02074 0.01209 -0.0810 0.3800 1.0000
7.250 1.2225 0.02102 0.01248 -0.0796 0.3511 1.0000
7.500 1.2382 0.02135 0.01285 -0.0777 0.3058 1.0000
7.750 1.2474 0.02263 0.01367 -0.0751 0.2149 1.0000
8.000 1.2445 0.02593 0.01582 -0.0717 0.0866 1.0000
8.250 1.2523 0.02800 0.01791 -0.0692 0.0731 1.0000
8.500 1.2560 0.03014 0.02013 -0.0662 0.0673 1.0000
8.750 1.2641 0.03172 0.02191 -0.0636 0.0638 1.0000
9.000 1.2679 0.03343 0.02376 -0.0606 0.0606 1.0000
9.250 1.2695 0.03540 0.02574 -0.0577 0.0575 1.0000
9.500 1.2754 0.03768 0.02796 -0.0551 0.0547 1.0000
9.750 1.2944 0.03939 0.02973 -0.0535 0.0528 1.0000
10.000 1.3271 0.04151 0.03189 -0.0533 0.0511 1.0000
10.250 1.3622 0.04412 0.03459 -0.0538 0.0492 1.0000
10.500 1.3883 0.04690 0.03748 -0.0536 0.0466 1.0000
10.750 1.4163 0.05035 0.04115 -0.0535 0.0461 1.0000
11.000 1.4337 0.05360 0.04479 -0.0519 0.0468 1.0000
11.250 1.4371 0.05690 0.04865 -0.0491 0.0481 1.0000
11.500 1.4357 0.06061 0.05285 -0.0461 0.0497 1.0000
11.750 1.4324 0.06461 0.05724 -0.0433 0.0514 1.0000
12.000 1.4269 0.06889 0.06183 -0.0408 0.0528 1.0000
12.250 1.4226 0.07400 0.06718 -0.0389 0.0541 1.0000
12.500 1.4354 0.07915 0.07254 -0.0382 0.0562 1.0000
12.750 1.4049 0.08071 0.07445 -0.0345 0.0571 1.0000
13.000 1.3650 0.08425 0.07837 -0.0330 0.0580 1.0000
13.250 1.3273 0.08961 0.08408 -0.0336 0.0591 1.0000
13.500 1.2949 0.09598 0.09072 -0.0358 0.0600 1.0000
13.750 1.2638 0.10315 0.09811 -0.0392 0.0606 1.0000
14.000 1.2328 0.11122 0.10636 -0.0440 0.0608 1.0000
14.250 1.2011 0.12051 0.11580 -0.0503 0.0607 1.0000
14.500 1.1654 0.13242 0.12783 -0.0590 0.0608 1.0000
14.750 1.1229 0.14939 0.14480 -0.0711 0.0626 1.0000
15.000 1.0990 0.16874 0.16412 -0.0809 0.0816 1.0000
15.250 0.8722 0.14720 0.14281 -0.0531 0.0650 1.0000
15.500 0.8674 0.15190 0.14751 -0.0543 0.0667 1.0000
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Polar data table (+)
Polar graphs
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