GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 361 AIRFOIL (goe361-il) Reynolds number: 200,000 Max Cl/Cd: 76.64 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe361-il-200000.txt Download as CSV file: xf-goe361-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 361 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2852 0.08925 0.08611 -0.0214 1.0000 0.0281
-6.750 -0.2859 0.08715 0.08406 -0.0202 1.0000 0.0285
-6.500 -0.2888 0.08532 0.08231 -0.0189 1.0000 0.0290
-6.250 -0.2926 0.08360 0.08065 -0.0176 1.0000 0.0297
-6.000 -0.2962 0.08193 0.07903 -0.0166 1.0000 0.0301
-5.750 -0.2899 0.07955 0.07668 -0.0182 0.9988 0.0312
-5.500 -0.2187 0.07460 0.07157 -0.0409 0.9904 0.0345
-5.250 -0.1716 0.06815 0.06502 -0.0532 0.9845 0.0351
-5.000 -0.1559 0.06364 0.06056 -0.0527 0.9785 0.0361
-4.750 -0.1225 0.05975 0.05663 -0.0575 0.9728 0.0379
-4.500 -0.0807 0.05572 0.05253 -0.0653 0.9655 0.0412
-4.250 -0.0087 0.04964 0.04612 -0.0822 0.9592 0.0458
-4.000 0.0179 0.04627 0.04278 -0.0841 0.9526 0.0477
-3.750 0.0589 0.04299 0.03942 -0.0895 0.9462 0.0517
-3.500 0.1188 0.03837 0.03444 -0.0996 0.9406 0.0587
-3.250 0.1493 0.03589 0.03196 -0.1017 0.9310 0.0623
-3.000 0.2012 0.03302 0.02857 -0.1079 0.9206 0.0715
-2.750 0.2299 0.03023 0.02588 -0.1095 0.9091 0.0746
-2.500 0.2709 0.02846 0.02362 -0.1123 0.8945 0.0858
-2.250 0.2947 0.02624 0.02147 -0.1125 0.8759 0.0900
-2.000 0.3255 0.02462 0.01953 -0.1131 0.8557 0.1019
-1.500 0.3775 0.02188 0.01644 -0.1126 0.8117 0.1204
-1.250 0.4040 0.02071 0.01504 -0.1124 0.7916 0.1342
-1.000 0.4303 0.01971 0.01384 -0.1121 0.7720 0.1510
-0.500 0.4805 0.01791 0.01173 -0.1113 0.7351 0.2058
-0.250 0.5225 0.01550 0.00814 -0.1099 0.7200 0.0797
0.000 0.5504 0.01481 0.00705 -0.1088 0.7022 0.0694
0.250 0.5767 0.01400 0.00605 -0.1082 0.6845 0.0669
0.500 0.6029 0.01347 0.00536 -0.1074 0.6670 0.0653
0.750 0.6288 0.01309 0.00484 -0.1066 0.6499 0.0647
1.000 0.6545 0.01281 0.00446 -0.1059 0.6331 0.0653
1.250 0.6802 0.01262 0.00421 -0.1052 0.6156 0.0671
1.500 0.7058 0.01253 0.00407 -0.1045 0.5980 0.0710
1.750 0.7313 0.01237 0.00386 -0.1039 0.5804 0.0744
2.000 0.7569 0.01236 0.00378 -0.1032 0.5627 0.0800
2.500 0.8145 0.01085 0.00380 -0.1036 0.5263 1.0000
2.750 0.8398 0.01108 0.00385 -0.1030 0.5078 1.0000
3.000 0.8649 0.01134 0.00396 -0.1023 0.4896 1.0000
3.250 0.8898 0.01163 0.00409 -0.1016 0.4719 1.0000
3.500 0.9147 0.01194 0.00427 -0.1010 0.4543 1.0000
3.750 0.9396 0.01226 0.00448 -0.1004 0.4374 1.0000
4.000 0.9644 0.01261 0.00475 -0.0997 0.4216 1.0000
4.250 0.9891 0.01299 0.00504 -0.0992 0.4071 1.0000
4.500 1.0139 0.01338 0.00535 -0.0986 0.3941 1.0000
5.000 1.0639 0.01415 0.00606 -0.0975 0.3720 1.0000
5.250 1.0890 0.01457 0.00646 -0.0970 0.3632 1.0000
5.500 1.1134 0.01493 0.00676 -0.0964 0.3525 1.0000
5.750 1.1371 0.01520 0.00700 -0.0957 0.3392 1.0000
6.000 1.1606 0.01542 0.00728 -0.0950 0.3257 1.0000
6.250 1.1844 0.01566 0.00758 -0.0943 0.3133 1.0000
6.500 1.2079 0.01593 0.00790 -0.0936 0.3005 1.0000
6.750 1.2303 0.01619 0.00817 -0.0927 0.2833 1.0000
7.000 1.2520 0.01647 0.00846 -0.0917 0.2558 1.0000
7.250 1.2716 0.01707 0.00886 -0.0904 0.2048 1.0000
7.750 1.2892 0.02128 0.01202 -0.0854 0.0399 1.0000
8.000 1.3049 0.02248 0.01341 -0.0836 0.0365 1.0000
8.250 1.3204 0.02356 0.01471 -0.0817 0.0347 1.0000
8.500 1.3325 0.02481 0.01612 -0.0795 0.0325 1.0000
8.750 1.3406 0.02626 0.01768 -0.0769 0.0308 1.0000
9.000 1.3450 0.02786 0.01939 -0.0738 0.0298 1.0000
9.250 1.3447 0.02956 0.02116 -0.0701 0.0291 1.0000
9.500 1.3433 0.03149 0.02316 -0.0665 0.0285 1.0000
9.750 1.3450 0.03354 0.02526 -0.0636 0.0281 1.0000
10.000 1.3522 0.03588 0.02761 -0.0613 0.0277 1.0000
10.250 1.3696 0.03829 0.03008 -0.0600 0.0271 1.0000
10.500 1.3792 0.03969 0.03163 -0.0582 0.0265 1.0000
10.750 1.3911 0.04140 0.03349 -0.0566 0.0258 1.0000
11.000 1.4118 0.04371 0.03594 -0.0557 0.0257 1.0000
11.250 1.4368 0.04665 0.03905 -0.0552 0.0259 1.0000
11.500 1.4992 0.05229 0.04485 -0.0595 0.0279 1.0000
11.750 1.4944 0.05262 0.04544 -0.0551 0.0289 1.0000
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Polar data table (+)
Polar graphs
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