GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il) Reynolds number: 100,000 Max Cl/Cd: 62.77 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe610bm-il-100000.txt Download as CSV file: xf-goe610bm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610-B MOD. 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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2995 0.09589 0.09149 -0.0273 1.0000 0.0560
-6.750 -0.3053 0.09532 0.09102 -0.0292 1.0000 0.0571
-6.500 -0.3090 0.09495 0.09074 -0.0326 1.0000 0.0577
-6.250 -0.3069 0.09400 0.08981 -0.0369 1.0000 0.0581
-6.000 -0.3109 0.08964 0.08555 -0.0341 1.0000 0.0588
-5.750 -0.3165 0.08595 0.08194 -0.0272 1.0000 0.0601
-5.500 -0.3180 0.08358 0.07962 -0.0247 1.0000 0.0615
-5.250 -0.3172 0.08139 0.07747 -0.0239 1.0000 0.0633
-5.000 -0.3130 0.07907 0.07518 -0.0246 1.0000 0.0656
-4.750 -0.3026 0.07652 0.07262 -0.0276 1.0000 0.0688
-4.500 -0.2485 0.07095 0.06685 -0.0443 0.9956 0.0737
-4.250 -0.2266 0.06687 0.06280 -0.0446 0.9900 0.0778
-4.000 -0.1642 0.06127 0.05696 -0.0597 0.9840 0.0889
-3.750 -0.1138 0.05698 0.05246 -0.0694 0.9770 0.1027
-3.500 -0.0648 0.05274 0.04803 -0.0775 0.9713 0.1171
-3.250 -0.0246 0.04898 0.04415 -0.0828 0.9643 0.1320
-3.000 0.0145 0.04559 0.04074 -0.0868 0.9581 0.1501
-2.750 0.0632 0.04296 0.03788 -0.0935 0.9510 0.1857
-1.750 0.2915 0.02811 0.02119 -0.1202 0.9282 0.1483
-1.500 0.3413 0.02497 0.01720 -0.1230 0.9198 0.1108
-1.250 0.3892 0.02302 0.01481 -0.1261 0.9132 0.1079
-1.000 0.4266 0.02181 0.01313 -0.1269 0.9015 0.1026
-0.750 0.4613 0.02086 0.01198 -0.1273 0.8895 0.1018
-0.500 0.4938 0.01981 0.01087 -0.1274 0.8771 0.1030
-0.250 0.5235 0.01901 0.01010 -0.1270 0.8636 0.1075
0.000 0.5517 0.01849 0.00952 -0.1261 0.8492 0.1157
0.250 0.5787 0.01789 0.00896 -0.1251 0.8343 0.1229
0.500 0.6062 0.01747 0.00850 -0.1242 0.8191 0.1373
0.750 0.6292 0.01557 0.00835 -0.1228 0.8049 0.7071
1.000 0.6550 0.01524 0.00785 -0.1209 0.7894 1.0000
1.250 0.6815 0.01534 0.00768 -0.1200 0.7744 1.0000
1.500 0.7081 0.01548 0.00762 -0.1192 0.7598 1.0000
1.750 0.7347 0.01567 0.00763 -0.1186 0.7456 1.0000
2.000 0.7613 0.01590 0.00771 -0.1180 0.7319 1.0000
2.250 0.7881 0.01617 0.00786 -0.1176 0.7189 1.0000
2.500 0.8149 0.01645 0.00806 -0.1172 0.7065 1.0000
2.750 0.8420 0.01673 0.00824 -0.1168 0.6953 1.0000
3.000 0.8690 0.01703 0.00846 -0.1165 0.6843 1.0000
3.250 0.8957 0.01740 0.00881 -0.1163 0.6727 1.0000
3.500 0.9225 0.01776 0.00919 -0.1161 0.6621 1.0000
3.750 0.9497 0.01807 0.00945 -0.1159 0.6531 1.0000
4.000 0.9764 0.01844 0.00984 -0.1157 0.6430 1.0000
4.250 1.0029 0.01883 0.01028 -0.1155 0.6328 1.0000
4.500 1.0293 0.01906 0.01054 -0.1150 0.6216 1.0000
4.750 1.0554 0.01920 0.01067 -0.1143 0.6088 1.0000
5.000 1.0812 0.01931 0.01077 -0.1136 0.5948 1.0000
5.250 1.1070 0.01947 0.01092 -0.1129 0.5810 1.0000
5.500 1.1331 0.01968 0.01117 -0.1122 0.5683 1.0000
5.750 1.1590 0.02000 0.01153 -0.1117 0.5563 1.0000
6.000 1.1844 0.02034 0.01197 -0.1112 0.5434 1.0000
6.250 1.2088 0.02048 0.01210 -0.1101 0.5247 1.0000
6.500 1.2320 0.02064 0.01235 -0.1090 0.5039 1.0000
6.750 1.2547 0.02070 0.01240 -0.1077 0.4803 1.0000
7.000 1.2763 0.02072 0.01243 -0.1063 0.4542 1.0000
7.250 1.2982 0.02090 0.01281 -0.1051 0.4314 1.0000
7.500 1.3193 0.02107 0.01310 -0.1038 0.4042 1.0000
7.750 1.3382 0.02132 0.01342 -0.1022 0.3647 1.0000
8.000 1.3560 0.02188 0.01391 -0.1006 0.3155 1.0000
8.250 1.3718 0.02282 0.01466 -0.0988 0.2612 1.0000
8.500 1.3811 0.02447 0.01587 -0.0965 0.1984 1.0000
8.750 1.3873 0.02649 0.01748 -0.0939 0.1477 1.0000
9.000 1.3946 0.02838 0.01912 -0.0913 0.0985 1.0000
9.500 1.3993 0.03253 0.02291 -0.0849 0.0489 1.0000
9.750 1.4007 0.03429 0.02478 -0.0814 0.0452 1.0000
10.000 1.4009 0.03619 0.02684 -0.0781 0.0428 1.0000
10.250 1.3998 0.03835 0.02915 -0.0752 0.0411 1.0000
10.500 1.3970 0.04082 0.03175 -0.0725 0.0399 1.0000
10.750 1.3929 0.04358 0.03463 -0.0701 0.0389 1.0000
11.000 1.3907 0.04634 0.03749 -0.0680 0.0380 1.0000
11.250 1.3933 0.04879 0.04011 -0.0662 0.0370 1.0000
11.500 1.3969 0.05126 0.04273 -0.0645 0.0357 1.0000
11.750 1.4019 0.05372 0.04532 -0.0628 0.0345 1.0000
12.000 1.4106 0.05607 0.04784 -0.0609 0.0340 1.0000
12.250 1.4232 0.05844 0.05036 -0.0590 0.0337 1.0000
12.500 1.4372 0.06110 0.05324 -0.0571 0.0336 1.0000
12.750 1.4482 0.06435 0.05677 -0.0554 0.0338 1.0000
13.000 1.4513 0.06824 0.06100 -0.0540 0.0342 1.0000
13.250 1.4469 0.07262 0.06573 -0.0529 0.0346 1.0000
13.500 1.4372 0.07739 0.07084 -0.0522 0.0350 1.0000
13.750 1.4235 0.08254 0.07630 -0.0522 0.0354 1.0000
14.000 1.4073 0.08804 0.08209 -0.0527 0.0358 1.0000
14.250 1.3891 0.09395 0.08828 -0.0540 0.0361 1.0000
14.500 1.3697 0.10025 0.09483 -0.0560 0.0364 1.0000
14.750 1.3492 0.10702 0.10183 -0.0588 0.0367 1.0000
15.000 1.3282 0.11430 0.10932 -0.0624 0.0370 1.0000
15.250 1.3068 0.12218 0.11739 -0.0669 0.0372 1.0000
15.500 1.2853 0.13074 0.12612 -0.0722 0.0375 1.0000
15.750 1.2640 0.13995 0.13548 -0.0782 0.0378 1.0000
16.000 1.2446 0.14956 0.14519 -0.0845 0.0381 1.0000
16.250 1.2235 0.16089 0.15666 -0.0927 0.0387 1.0000
16.500 1.1562 0.19756 0.19318 -0.1173 0.0453 1.0000
16.750 1.1600 0.20269 0.19830 -0.1193 0.0470 1.0000
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Polar data table (+)
Polar graphs
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