GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 414 AIRFOIL (goe414-il) Reynolds number: 1,000,000 Max Cl/Cd: 119 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe414-il-1000000-n5.txt Download as CSV file: xf-goe414-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5198 0.10450 0.10255 -0.0609 1.0000 0.0065
-14.500 -0.5418 0.09547 0.09345 -0.0667 0.9959 0.0065
-14.000 -0.8319 0.03242 0.02955 -0.1202 0.9490 0.0054
-13.750 -0.8299 0.02906 0.02596 -0.1216 0.9404 0.0055
-13.500 -0.8204 0.02693 0.02364 -0.1217 0.9336 0.0056
-13.250 -0.8065 0.02524 0.02180 -0.1216 0.9268 0.0058
-13.000 -0.7905 0.02385 0.02024 -0.1214 0.9205 0.0059
-12.750 -0.7722 0.02265 0.01889 -0.1211 0.9146 0.0060
-12.500 -0.7526 0.02162 0.01772 -0.1208 0.9076 0.0061
-12.250 -0.7333 0.02049 0.01644 -0.1205 0.9010 0.0063
-12.000 -0.7134 0.01936 0.01517 -0.1201 0.8943 0.0066
-11.750 -0.6919 0.01847 0.01416 -0.1198 0.8889 0.0068
-11.500 -0.6690 0.01769 0.01328 -0.1196 0.8834 0.0071
-11.250 -0.6457 0.01700 0.01248 -0.1193 0.8771 0.0073
-11.000 -0.6218 0.01637 0.01173 -0.1191 0.8705 0.0076
-10.750 -0.5976 0.01579 0.01104 -0.1188 0.8628 0.0079
-10.500 -0.5729 0.01526 0.01040 -0.1186 0.8555 0.0082
-10.250 -0.5478 0.01478 0.00980 -0.1184 0.8485 0.0084
-10.000 -0.5229 0.01421 0.00914 -0.1182 0.8423 0.0089
-9.750 -0.4975 0.01372 0.00857 -0.1180 0.8357 0.0095
-9.500 -0.4717 0.01330 0.00806 -0.1179 0.8296 0.0101
-9.250 -0.4455 0.01293 0.00761 -0.1178 0.8226 0.0108
-9.000 -0.4192 0.01260 0.00718 -0.1176 0.8161 0.0114
-8.750 -0.3928 0.01221 0.00675 -0.1176 0.8093 0.0125
-8.500 -0.3663 0.01191 0.00640 -0.1174 0.8021 0.0136
-8.250 -0.3393 0.01163 0.00606 -0.1174 0.7948 0.0146
-8.000 -0.3126 0.01138 0.00572 -0.1173 0.7867 0.0156
-7.750 -0.2855 0.01113 0.00546 -0.1173 0.7781 0.0171
-7.500 -0.2583 0.01096 0.00523 -0.1172 0.7698 0.0186
-7.250 -0.2308 0.01080 0.00502 -0.1172 0.7607 0.0197
-7.000 -0.2035 0.01065 0.00480 -0.1172 0.7508 0.0204
-6.750 -0.1770 0.01039 0.00445 -0.1170 0.7384 0.0218
-6.500 -0.1502 0.01023 0.00422 -0.1168 0.7232 0.0230
-6.250 -0.1234 0.01012 0.00402 -0.1167 0.7066 0.0243
-6.000 -0.0966 0.01001 0.00381 -0.1165 0.6910 0.0253
-5.750 -0.0697 0.00993 0.00363 -0.1164 0.6761 0.0261
-5.500 -0.0428 0.00986 0.00348 -0.1163 0.6623 0.0266
-5.250 -0.0160 0.00974 0.00326 -0.1161 0.6502 0.0275
-5.000 0.0109 0.00958 0.00301 -0.1160 0.6395 0.0292
-4.750 0.0383 0.00944 0.00282 -0.1159 0.6318 0.0307
-4.500 0.0656 0.00932 0.00265 -0.1159 0.6242 0.0320
-4.250 0.0933 0.00923 0.00251 -0.1159 0.6176 0.0331
-4.000 0.1209 0.00915 0.00237 -0.1159 0.6104 0.0344
-3.750 0.1485 0.00908 0.00226 -0.1159 0.6037 0.0367
-3.500 0.1760 0.00897 0.00214 -0.1159 0.5967 0.0419
-3.250 0.2030 0.00881 0.00205 -0.1158 0.5901 0.0648
-3.000 0.2308 0.00874 0.00199 -0.1159 0.5836 0.0733
-2.750 0.2585 0.00873 0.00193 -0.1159 0.5765 0.0771
-2.500 0.2864 0.00870 0.00188 -0.1159 0.5694 0.0799
-2.250 0.3139 0.00868 0.00183 -0.1159 0.5610 0.0843
-2.000 0.3416 0.00866 0.00179 -0.1160 0.5521 0.0890
-1.750 0.3689 0.00867 0.00176 -0.1159 0.5417 0.0922
-1.500 0.3960 0.00868 0.00173 -0.1158 0.5288 0.0987
-1.250 0.4227 0.00872 0.00172 -0.1157 0.5126 0.1047
-1.000 0.4489 0.00879 0.00173 -0.1155 0.4927 0.1130
-0.750 0.4745 0.00889 0.00175 -0.1152 0.4721 0.1240
-0.250 0.5268 0.00900 0.00182 -0.1148 0.4453 0.1590
0.000 0.5531 0.00898 0.00187 -0.1146 0.4368 0.1936
0.250 0.5794 0.00894 0.00193 -0.1145 0.4296 0.2437
0.500 0.6061 0.00896 0.00199 -0.1145 0.4239 0.2722
0.750 0.6333 0.00898 0.00204 -0.1145 0.4200 0.2914
1.000 0.6604 0.00900 0.00210 -0.1144 0.4164 0.3097
1.250 0.6873 0.00904 0.00217 -0.1144 0.4128 0.3305
1.500 0.7141 0.00907 0.00225 -0.1143 0.4095 0.3552
1.750 0.7412 0.00906 0.00232 -0.1143 0.4068 0.3868
2.000 0.7677 0.00899 0.00240 -0.1143 0.4038 0.4474
2.250 0.7833 0.00799 0.00262 -0.1120 0.4010 0.8882
2.500 0.8392 0.00807 0.00280 -0.1183 0.3972 0.9988
3.000 0.8910 0.00827 0.00297 -0.1178 0.3931 1.0000
3.250 0.9164 0.00836 0.00305 -0.1174 0.3911 1.0000
3.500 0.9417 0.00845 0.00314 -0.1170 0.3887 1.0000
3.750 0.9669 0.00856 0.00325 -0.1166 0.3860 1.0000
4.000 0.9919 0.00869 0.00336 -0.1162 0.3831 1.0000
4.250 1.0165 0.00884 0.00348 -0.1157 0.3796 1.0000
4.500 1.0422 0.00893 0.00359 -0.1154 0.3758 1.0000
4.750 1.0669 0.00908 0.00371 -0.1150 0.3680 1.0000
5.000 1.0914 0.00924 0.00385 -0.1145 0.3618 1.0000
5.250 1.1162 0.00939 0.00398 -0.1141 0.3541 1.0000
5.500 1.1400 0.00958 0.00414 -0.1136 0.3439 1.0000
5.750 1.1627 0.00983 0.00432 -0.1128 0.3278 1.0000
6.000 1.1823 0.01024 0.00458 -0.1115 0.2992 1.0000
6.250 1.1925 0.01113 0.00516 -0.1086 0.2465 1.0000
6.500 1.2045 0.01182 0.00567 -0.1059 0.2155 1.0000
6.750 1.2190 0.01239 0.00612 -0.1038 0.1937 1.0000
7.000 1.2215 0.01361 0.00698 -0.0997 0.1306 1.0000
7.250 1.2260 0.01476 0.00792 -0.0961 0.0872 1.0000
7.500 1.2219 0.01643 0.00926 -0.0913 0.0188 1.0000
7.750 1.2390 0.01696 0.00980 -0.0899 0.0145 1.0000
8.000 1.2565 0.01747 0.01033 -0.0886 0.0130 1.0000
8.250 1.2731 0.01805 0.01092 -0.0872 0.0117 1.0000
8.500 1.2888 0.01868 0.01159 -0.0858 0.0105 1.0000
8.750 1.3054 0.01927 0.01221 -0.0845 0.0100 1.0000
9.000 1.3213 0.01992 0.01289 -0.0832 0.0094 1.0000
9.250 1.3365 0.02063 0.01362 -0.0818 0.0087 1.0000
9.500 1.3503 0.02143 0.01445 -0.0804 0.0081 1.0000
9.750 1.3622 0.02239 0.01545 -0.0787 0.0075 1.0000
10.000 1.3759 0.02325 0.01635 -0.0774 0.0073 1.0000
10.250 1.3888 0.02417 0.01732 -0.0760 0.0070 1.0000
10.500 1.4009 0.02518 0.01838 -0.0746 0.0067 1.0000
10.750 1.4122 0.02628 0.01952 -0.0732 0.0064 1.0000
11.000 1.4229 0.02745 0.02074 -0.0719 0.0061 1.0000
11.250 1.4327 0.02871 0.02204 -0.0705 0.0059 1.0000
11.500 1.4409 0.03014 0.02351 -0.0691 0.0056 1.0000
11.750 1.4457 0.03190 0.02533 -0.0676 0.0053 1.0000
12.000 1.4540 0.03341 0.02691 -0.0664 0.0052 1.0000
12.250 1.4613 0.03505 0.02861 -0.0653 0.0050 1.0000
12.500 1.4674 0.03687 0.03050 -0.0641 0.0049 1.0000
12.750 1.4724 0.03885 0.03255 -0.0631 0.0048 1.0000
13.000 1.4772 0.04092 0.03469 -0.0622 0.0046 1.0000
13.250 1.4809 0.04316 0.03700 -0.0613 0.0045 1.0000
13.500 1.4839 0.04553 0.03944 -0.0606 0.0044 1.0000
13.750 1.4864 0.04801 0.04199 -0.0599 0.0043 1.0000
14.000 1.4883 0.05062 0.04467 -0.0593 0.0042 1.0000
14.250 1.4897 0.05334 0.04746 -0.0589 0.0041 1.0000
14.500 1.4893 0.05628 0.05047 -0.0584 0.0040 1.0000
14.750 1.4879 0.05939 0.05366 -0.0580 0.0039 1.0000
15.000 1.4850 0.06275 0.05710 -0.0577 0.0038 1.0000
15.250 1.4805 0.06637 0.06082 -0.0576 0.0037 1.0000
15.500 1.4733 0.07037 0.06491 -0.0574 0.0037 1.0000
15.750 1.4663 0.07443 0.06906 -0.0575 0.0036 1.0000
16.000 1.4626 0.07813 0.07285 -0.0576 0.0036 1.0000
16.250 1.4585 0.08193 0.07674 -0.0579 0.0035 1.0000
16.500 1.4545 0.08575 0.08065 -0.0582 0.0035 1.0000
16.750 1.4498 0.08967 0.08466 -0.0586 0.0035 1.0000
17.000 1.4454 0.09360 0.08867 -0.0590 0.0034 1.0000
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