GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 264 AIRFOIL (goe264-il) Reynolds number: 100,000 Max Cl/Cd: 59.94 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe264-il-100000.txt Download as CSV file: xf-goe264-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 264 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3093 0.10425 0.09946 -0.0228 1.0000 0.0580
-7.750 -0.3129 0.10394 0.09926 -0.0248 1.0000 0.0588
-7.500 -0.3122 0.10364 0.09904 -0.0294 1.0000 0.0593
-7.250 -0.3075 0.10276 0.09821 -0.0343 1.0000 0.0595
-7.000 -0.3034 0.09878 0.09430 -0.0347 1.0000 0.0599
-6.750 -0.3012 0.09214 0.08771 -0.0273 1.0000 0.0611
-6.500 -0.2981 0.08891 0.08453 -0.0251 1.0000 0.0624
-6.250 -0.2958 0.08644 0.08211 -0.0242 1.0000 0.0639
-6.000 -0.2933 0.08417 0.07986 -0.0241 1.0000 0.0657
-5.750 -0.2893 0.08197 0.07771 -0.0247 1.0000 0.0682
-5.500 -0.2707 0.08123 0.07692 -0.0328 1.0000 0.0725
-5.250 -0.2528 0.07848 0.07412 -0.0388 1.0000 0.0737
-5.000 -0.2567 0.07438 0.07012 -0.0339 1.0000 0.0748
-4.750 -0.2531 0.07151 0.06731 -0.0318 1.0000 0.0766
-4.500 -0.2435 0.06902 0.06483 -0.0322 1.0000 0.0793
-4.250 -0.1865 0.06900 0.06440 -0.0475 1.0000 0.0871
-4.000 -0.1884 0.06340 0.05902 -0.0439 0.9987 0.0885
-3.750 -0.1241 0.06042 0.05573 -0.0555 0.9912 0.1007
-3.500 -0.0881 0.05450 0.04983 -0.0605 0.9847 0.1040
-3.250 -0.0259 0.05113 0.04616 -0.0710 0.9763 0.1169
-2.750 0.0686 0.04367 0.03846 -0.0833 0.9604 0.1362
-2.500 0.1227 0.04061 0.03520 -0.0905 0.9528 0.1519
-2.250 0.1834 0.03840 0.03262 -0.0985 0.9442 0.1733
-2.000 0.2302 0.03529 0.02940 -0.1036 0.9351 0.1888
-0.750 0.4672 0.02421 0.01659 -0.1208 0.8761 0.1426
-0.500 0.5010 0.02269 0.01484 -0.1211 0.8597 0.1413
-0.250 0.5334 0.02121 0.01304 -0.1209 0.8428 0.1350
0.000 0.5640 0.02006 0.01153 -0.1202 0.8254 0.1326
0.250 0.5913 0.01927 0.01057 -0.1193 0.8047 0.1345
0.500 0.6184 0.01871 0.00982 -0.1183 0.7845 0.1410
0.750 0.6451 0.01816 0.00915 -0.1173 0.7654 0.1500
1.000 0.6715 0.01775 0.00857 -0.1163 0.7436 0.1577
1.250 0.6977 0.01727 0.00803 -0.1154 0.7241 0.1698
1.500 0.7230 0.01691 0.00766 -0.1142 0.7047 0.1929
1.750 0.7494 0.01656 0.00732 -0.1135 0.6852 0.2386
2.000 0.7740 0.01520 0.00709 -0.1128 0.6678 0.6907
2.250 0.7968 0.01510 0.00686 -0.1107 0.6509 1.0000
2.500 0.8237 0.01549 0.00696 -0.1102 0.6343 1.0000
2.750 0.8505 0.01591 0.00721 -0.1098 0.6181 1.0000
3.000 0.8773 0.01635 0.00751 -0.1095 0.6028 1.0000
3.250 0.9041 0.01681 0.00783 -0.1092 0.5885 1.0000
3.500 0.9308 0.01726 0.00822 -0.1089 0.5748 1.0000
3.750 0.9574 0.01771 0.00864 -0.1087 0.5616 1.0000
4.000 0.9840 0.01820 0.00913 -0.1085 0.5496 1.0000
4.250 1.0108 0.01870 0.00962 -0.1083 0.5389 1.0000
4.750 1.0640 0.01969 0.01067 -0.1080 0.5189 1.0000
5.000 1.0905 0.02024 0.01128 -0.1078 0.5099 1.0000
5.250 1.1174 0.02078 0.01185 -0.1076 0.5022 1.0000
5.500 1.1434 0.02143 0.01267 -0.1075 0.4938 1.0000
5.750 1.1703 0.02196 0.01323 -0.1073 0.4868 1.0000
6.000 1.1955 0.02264 0.01412 -0.1071 0.4782 1.0000
6.250 1.2226 0.02311 0.01459 -0.1068 0.4711 1.0000
6.500 1.2471 0.02325 0.01483 -0.1060 0.4568 1.0000
6.750 1.2683 0.02282 0.01443 -0.1043 0.4316 1.0000
7.000 1.2904 0.02260 0.01419 -0.1029 0.4094 1.0000
7.250 1.3111 0.02243 0.01410 -0.1013 0.3852 1.0000
7.500 1.3282 0.02216 0.01403 -0.0992 0.3479 1.0000
7.750 1.3297 0.02336 0.01436 -0.0951 0.1572 1.0000
8.000 1.3264 0.02719 0.01738 -0.0914 0.0817 1.0000
8.250 1.3344 0.02928 0.01948 -0.0887 0.0692 1.0000
8.500 1.3415 0.03116 0.02149 -0.0859 0.0623 1.0000
8.750 1.3434 0.03321 0.02363 -0.0827 0.0581 1.0000
9.000 1.3404 0.03547 0.02591 -0.0788 0.0560 1.0000
9.250 1.3442 0.03723 0.02779 -0.0755 0.0544 1.0000
9.500 1.3529 0.03912 0.02973 -0.0728 0.0526 1.0000
9.750 1.3677 0.04107 0.03174 -0.0708 0.0500 1.0000
10.000 1.3900 0.04346 0.03403 -0.0700 0.0467 1.0000
10.250 1.4510 0.04902 0.03948 -0.0740 0.0448 1.0000
10.500 1.4754 0.05263 0.04336 -0.0734 0.0447 1.0000
10.750 1.4952 0.05644 0.04751 -0.0724 0.0449 1.0000
11.000 1.5071 0.06045 0.05191 -0.0708 0.0449 1.0000
11.250 1.5096 0.06415 0.05597 -0.0683 0.0446 1.0000
11.500 1.5069 0.06730 0.05950 -0.0653 0.0445 1.0000
11.750 1.5114 0.07229 0.06482 -0.0636 0.0449 1.0000
12.000 1.5054 0.07354 0.06638 -0.0600 0.0455 1.0000
12.250 1.4873 0.07506 0.06826 -0.0553 0.0464 1.0000
12.500 1.4564 0.07819 0.07181 -0.0518 0.0473 1.0000
12.750 1.4261 0.08270 0.07671 -0.0503 0.0483 1.0000
13.000 1.3986 0.08810 0.08244 -0.0503 0.0494 1.0000
13.250 1.3724 0.09410 0.08873 -0.0517 0.0502 1.0000
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Polar data table (+)
Polar graphs
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