GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 414 AIRFOIL (goe414-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.9 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe414-il-1000000.txt Download as CSV file: xf-goe414-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 414 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.1614 0.13999 0.13841 -0.0622 0.9925 0.0130
-14.500 -0.1538 0.13728 0.13570 -0.0641 0.9906 0.0135
-13.250 -0.7504 0.03146 0.02878 -0.1237 0.9812 0.0102
-13.000 -0.7390 0.02900 0.02616 -0.1253 0.9737 0.0104
-12.750 -0.7263 0.02716 0.02417 -0.1257 0.9668 0.0106
-12.500 -0.7132 0.02569 0.02255 -0.1252 0.9596 0.0108
-12.250 -0.6983 0.02434 0.02105 -0.1246 0.9532 0.0111
-12.000 -0.6823 0.02310 0.01966 -0.1239 0.9466 0.0113
-11.750 -0.6641 0.02204 0.01843 -0.1233 0.9414 0.0116
-11.500 -0.6439 0.02113 0.01739 -0.1229 0.9358 0.0118
-11.250 -0.6240 0.02018 0.01630 -0.1223 0.9301 0.0120
-11.000 -0.6087 0.01851 0.01443 -0.1214 0.9242 0.0126
-10.750 -0.5853 0.01794 0.01380 -0.1211 0.9181 0.0131
-10.500 -0.5610 0.01751 0.01330 -0.1207 0.9127 0.0135
-10.250 -0.5361 0.01707 0.01280 -0.1205 0.9070 0.0140
-10.000 -0.5116 0.01656 0.01219 -0.1202 0.9012 0.0145
-9.500 -0.4607 0.01570 0.01112 -0.1198 0.8908 0.0153
-9.250 -0.4396 0.01454 0.00982 -0.1192 0.8846 0.0162
-9.000 -0.4135 0.01421 0.00944 -0.1190 0.8787 0.0168
-8.750 -0.3871 0.01390 0.00908 -0.1189 0.8722 0.0175
-8.500 -0.3607 0.01358 0.00867 -0.1188 0.8667 0.0183
-8.250 -0.3334 0.01335 0.00838 -0.1187 0.8610 0.0190
-8.000 -0.3085 0.01271 0.00762 -0.1184 0.8551 0.0199
-7.750 -0.2826 0.01228 0.00714 -0.1183 0.8492 0.0209
-7.500 -0.2557 0.01200 0.00682 -0.1182 0.8422 0.0218
-7.250 -0.2288 0.01174 0.00648 -0.1181 0.8358 0.0228
-7.000 -0.2015 0.01151 0.00619 -0.1180 0.8287 0.0237
-6.500 -0.1494 0.01059 0.00511 -0.1176 0.8145 0.0262
-6.250 -0.1225 0.01033 0.00477 -0.1175 0.8071 0.0274
-6.000 -0.0952 0.01006 0.00446 -0.1174 0.7994 0.0286
-5.750 -0.0681 0.00988 0.00418 -0.1173 0.7912 0.0296
-5.500 -0.0407 0.00966 0.00391 -0.1172 0.7817 0.0305
-5.250 -0.0143 0.00927 0.00343 -0.1170 0.7723 0.0326
-5.000 0.0126 0.00905 0.00314 -0.1168 0.7620 0.0343
-4.750 0.0399 0.00887 0.00290 -0.1167 0.7509 0.0361
-4.500 0.0672 0.00874 0.00268 -0.1166 0.7391 0.0374
-4.250 0.0941 0.00856 0.00245 -0.1164 0.7264 0.0415
-4.000 0.1207 0.00836 0.00227 -0.1162 0.7133 0.0539
-3.750 0.1475 0.00824 0.00219 -0.1160 0.7002 0.0764
-3.250 0.2021 0.00820 0.00206 -0.1159 0.6757 0.0903
-3.000 0.2296 0.00820 0.00200 -0.1158 0.6653 0.0940
-2.750 0.2567 0.00817 0.00193 -0.1157 0.6556 0.1000
-2.500 0.2843 0.00814 0.00187 -0.1157 0.6466 0.1049
-2.250 0.3118 0.00813 0.00182 -0.1156 0.6385 0.1096
-2.000 0.3392 0.00809 0.00177 -0.1156 0.6305 0.1179
-1.750 0.3666 0.00805 0.00173 -0.1156 0.6231 0.1285
-1.500 0.3939 0.00798 0.00170 -0.1156 0.6154 0.1470
-1.250 0.4209 0.00789 0.00167 -0.1155 0.6079 0.1777
-1.000 0.4477 0.00776 0.00167 -0.1154 0.5997 0.2298
-0.750 0.4747 0.00769 0.00168 -0.1154 0.5916 0.2699
-0.500 0.5016 0.00767 0.00170 -0.1153 0.5823 0.3033
-0.250 0.5289 0.00765 0.00172 -0.1153 0.5719 0.3295
0.000 0.5557 0.00766 0.00174 -0.1152 0.5602 0.3537
0.250 0.5822 0.00768 0.00177 -0.1150 0.5458 0.3811
0.500 0.6083 0.00769 0.00181 -0.1148 0.5290 0.4158
0.750 0.6334 0.00767 0.00187 -0.1144 0.5088 0.4762
1.000 0.6554 0.00740 0.00198 -0.1136 0.4893 0.6558
1.250 0.6726 0.00698 0.00214 -0.1113 0.4742 0.8819
1.750 0.7696 0.00730 0.00243 -0.1207 0.4516 1.0000
2.000 0.7929 0.00746 0.00252 -0.1198 0.4449 1.0000
2.250 0.8174 0.00756 0.00259 -0.1192 0.4401 1.0000
2.500 0.8414 0.00768 0.00268 -0.1185 0.4354 1.0000
2.750 0.8649 0.00784 0.00279 -0.1177 0.4308 1.0000
3.000 0.8895 0.00795 0.00288 -0.1172 0.4274 1.0000
3.250 0.9144 0.00805 0.00298 -0.1167 0.4244 1.0000
3.500 0.9392 0.00817 0.00308 -0.1162 0.4214 1.0000
3.750 0.9636 0.00831 0.00320 -0.1156 0.4181 1.0000
4.000 0.9874 0.00850 0.00335 -0.1149 0.4137 1.0000
4.250 1.0134 0.00857 0.00345 -0.1147 0.4106 1.0000
4.500 1.0386 0.00869 0.00356 -0.1143 0.4065 1.0000
4.750 1.0624 0.00888 0.00372 -0.1137 0.4005 1.0000
5.000 1.0877 0.00900 0.00384 -0.1133 0.3961 1.0000
5.250 1.1133 0.00911 0.00396 -0.1130 0.3918 1.0000
5.500 1.1377 0.00927 0.00411 -0.1126 0.3871 1.0000
5.750 1.1622 0.00943 0.00426 -0.1121 0.3813 1.0000
6.000 1.1874 0.00954 0.00439 -0.1118 0.3746 1.0000
6.250 1.2110 0.00974 0.00455 -0.1112 0.3665 1.0000
6.500 1.2353 0.00989 0.00471 -0.1107 0.3571 1.0000
6.750 1.2587 0.01010 0.00488 -0.1101 0.3448 1.0000
7.000 1.2776 0.01050 0.00514 -0.1087 0.3140 1.0000
7.250 1.2775 0.01174 0.00591 -0.1039 0.2410 1.0000
7.500 1.2813 0.01286 0.00674 -0.1000 0.1940 1.0000
7.750 1.2686 0.01490 0.00823 -0.0936 0.0994 1.0000
8.000 1.2576 0.01697 0.00989 -0.0879 0.0231 1.0000
8.250 1.2723 0.01764 0.01057 -0.0861 0.0183 1.0000
8.500 1.2870 0.01833 0.01129 -0.0844 0.0164 1.0000
8.750 1.3008 0.01910 0.01210 -0.0827 0.0151 1.0000
9.000 1.3160 0.01978 0.01283 -0.0812 0.0144 1.0000
9.250 1.3301 0.02055 0.01364 -0.0797 0.0136 1.0000
9.500 1.3427 0.02144 0.01457 -0.0780 0.0129 1.0000
9.750 1.3523 0.02255 0.01573 -0.0761 0.0122 1.0000
10.000 1.3576 0.02400 0.01728 -0.0737 0.0116 1.0000
10.250 1.3697 0.02501 0.01834 -0.0723 0.0114 1.0000
10.500 1.3800 0.02618 0.01957 -0.0708 0.0111 1.0000
10.750 1.3890 0.02749 0.02094 -0.0692 0.0107 1.0000
11.000 1.3970 0.02892 0.02243 -0.0677 0.0104 1.0000
11.250 1.4040 0.03045 0.02402 -0.0662 0.0101 1.0000
11.500 1.4103 0.03211 0.02573 -0.0648 0.0097 1.0000
11.750 1.4143 0.03401 0.02769 -0.0633 0.0094 1.0000
12.000 1.4131 0.03648 0.03025 -0.0617 0.0092 1.0000
12.250 1.4021 0.04003 0.03393 -0.0598 0.0089 1.0000
12.500 1.4006 0.04283 0.03682 -0.0587 0.0087 1.0000
12.750 1.4055 0.04504 0.03909 -0.0580 0.0086 1.0000
13.000 1.4078 0.04756 0.04169 -0.0573 0.0085 1.0000
13.250 1.4089 0.05029 0.04450 -0.0567 0.0083 1.0000
13.500 1.4086 0.05324 0.04752 -0.0562 0.0082 1.0000
13.750 1.4074 0.05632 0.05069 -0.0557 0.0080 1.0000
14.000 1.4053 0.05954 0.05399 -0.0553 0.0079 1.0000
14.250 1.4034 0.06280 0.05732 -0.0550 0.0077 1.0000
14.500 1.4014 0.06612 0.06073 -0.0548 0.0076 1.0000
14.750 1.3995 0.06946 0.06414 -0.0547 0.0075 1.0000
15.000 1.3972 0.07288 0.06762 -0.0546 0.0073 1.0000
15.250 1.3949 0.07632 0.07114 -0.0546 0.0072 1.0000
15.500 1.3927 0.07981 0.07469 -0.0547 0.0071 1.0000
15.750 1.3908 0.08329 0.07824 -0.0549 0.0070 1.0000
16.000 1.3887 0.08679 0.08179 -0.0551 0.0069 1.0000
16.250 1.3862 0.09028 0.08533 -0.0552 0.0068 1.0000
16.500 1.3830 0.09380 0.08891 -0.0553 0.0067 1.0000
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Polar data table (+)
Polar graphs
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