GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 450 AIRFOIL (goe450-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.42 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe450-il-1000000.txt Download as CSV file: xf-goe450-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 450 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2332 0.08290 0.08123 -0.0668 0.9820 0.0169
-8.250 -0.2295 0.07781 0.07614 -0.0703 0.9730 0.0171
-8.000 -0.2183 0.07579 0.07412 -0.0707 0.9660 0.0173
-7.750 -0.2078 0.07347 0.07178 -0.0721 0.9582 0.0176
-7.500 -0.1954 0.07082 0.06912 -0.0747 0.9504 0.0179
-7.250 -0.1818 0.06782 0.06609 -0.0780 0.9428 0.0184
-7.000 -0.1654 0.06428 0.06252 -0.0826 0.9349 0.0193
-6.750 -0.1358 0.05631 0.05443 -0.0960 0.9261 0.0208
-6.500 -0.1110 0.05011 0.04813 -0.1035 0.9185 0.0209
-6.250 -0.0945 0.04422 0.04212 -0.1087 0.9119 0.0214
-6.000 -0.0722 0.04212 0.03996 -0.1106 0.9056 0.0218
-5.750 -0.0485 0.03973 0.03748 -0.1127 0.8994 0.0223
-5.500 -0.0227 0.03672 0.03435 -0.1154 0.8931 0.0232
-5.250 0.0090 0.02396 0.02076 -0.1222 0.8860 0.0263
-5.000 0.0334 0.02255 0.01926 -0.1226 0.8800 0.0267
-4.750 0.0588 0.02151 0.01815 -0.1230 0.8729 0.0271
-4.500 0.0846 0.02039 0.01688 -0.1232 0.8663 0.0278
-4.250 0.1111 0.01901 0.01535 -0.1235 0.8583 0.0291
-4.000 0.1406 0.01922 0.01528 -0.1230 0.8504 0.0317
-3.750 0.1674 0.01783 0.01361 -0.1231 0.8411 0.0318
-3.500 -0.0614 0.02285 0.02064 -0.1245 0.8602 0.0276
-2.750 0.2742 0.01111 0.00597 -0.1231 0.7998 0.0310
-2.500 0.3015 0.01026 0.00495 -0.1230 0.7876 0.0308
-2.250 0.3289 0.00974 0.00430 -0.1228 0.7750 0.0309
-2.000 0.3563 0.00934 0.00379 -0.1226 0.7624 0.0310
-1.750 0.3838 0.00898 0.00335 -0.1225 0.7498 0.0311
-1.500 0.4112 0.00867 0.00298 -0.1224 0.7372 0.0313
-1.250 0.4386 0.00843 0.00267 -0.1222 0.7249 0.0314
-1.000 0.4661 0.00832 0.00249 -0.1221 0.7132 0.0317
-0.500 0.5209 0.00773 0.00179 -0.1219 0.6905 0.0329
-0.250 0.5485 0.00759 0.00159 -0.1219 0.6797 0.0340
0.000 0.5761 0.00753 0.00148 -0.1218 0.6689 0.0349
0.250 0.6035 0.00751 0.00141 -0.1217 0.6572 0.0359
0.500 0.6312 0.00748 0.00135 -0.1216 0.6463 0.0369
0.750 0.6588 0.00748 0.00132 -0.1216 0.6366 0.0382
1.250 0.7138 0.00750 0.00129 -0.1214 0.6146 0.0479
1.500 0.7412 0.00719 0.00138 -0.1215 0.6053 0.2337
1.750 0.7679 0.00675 0.00154 -0.1217 0.5964 0.5085
2.000 0.7925 0.00577 0.00166 -0.1211 0.5880 1.0000
2.250 0.8197 0.00589 0.00172 -0.1209 0.5767 1.0000
2.500 0.8464 0.00603 0.00178 -0.1207 0.5590 1.0000
2.750 0.8730 0.00619 0.00185 -0.1205 0.5403 1.0000
3.000 0.8994 0.00636 0.00194 -0.1203 0.5220 1.0000
3.250 0.9257 0.00655 0.00204 -0.1200 0.5036 1.0000
3.500 0.9519 0.00675 0.00215 -0.1198 0.4825 1.0000
3.750 0.9776 0.00699 0.00229 -0.1194 0.4609 1.0000
4.000 1.0032 0.00723 0.00244 -0.1191 0.4393 1.0000
4.250 1.0277 0.00757 0.00263 -0.1186 0.4097 1.0000
4.500 1.0522 0.00791 0.00284 -0.1181 0.3823 1.0000
4.750 1.0773 0.00819 0.00304 -0.1177 0.3601 1.0000
5.000 1.1018 0.00852 0.00325 -0.1172 0.3371 1.0000
5.250 1.1255 0.00892 0.00351 -0.1166 0.3069 1.0000
5.500 1.1474 0.00948 0.00384 -0.1157 0.2629 1.0000
5.750 1.1633 0.01057 0.00446 -0.1139 0.1777 1.0000
6.000 1.1831 0.01129 0.00496 -0.1127 0.1382 1.0000
6.250 1.1989 0.01236 0.00565 -0.1108 0.0717 1.0000
6.500 1.2178 0.01311 0.00620 -0.1095 0.0391 1.0000
6.750 1.2399 0.01357 0.00664 -0.1086 0.0340 1.0000
7.000 1.2626 0.01395 0.00704 -0.1078 0.0318 1.0000
7.250 1.2852 0.01432 0.00745 -0.1070 0.0304 1.0000
7.500 1.3068 0.01475 0.00791 -0.1060 0.0287 1.0000
7.750 1.3266 0.01531 0.00850 -0.1048 0.0266 1.0000
8.000 1.3455 0.01591 0.00915 -0.1034 0.0251 1.0000
8.250 1.3668 0.01628 0.00955 -0.1024 0.0243 1.0000
8.500 1.3870 0.01671 0.01001 -0.1012 0.0231 1.0000
8.750 1.4058 0.01718 0.01050 -0.0999 0.0219 1.0000
9.000 1.4200 0.01782 0.01118 -0.0977 0.0205 1.0000
9.250 1.4308 0.01868 0.01210 -0.0950 0.0195 1.0000
9.500 1.4489 0.01910 0.01256 -0.0936 0.0188 1.0000
9.750 1.4653 0.01963 0.01313 -0.0919 0.0180 1.0000
10.000 1.4813 0.02018 0.01372 -0.0903 0.0172 1.0000
10.250 1.4966 0.02080 0.01435 -0.0886 0.0164 1.0000
10.500 1.5022 0.02205 0.01566 -0.0856 0.0154 1.0000
10.750 1.5160 0.02279 0.01646 -0.0839 0.0149 1.0000
11.000 1.5302 0.02353 0.01726 -0.0823 0.0144 1.0000
11.250 1.5431 0.02437 0.01815 -0.0806 0.0139 1.0000
11.500 1.5555 0.02527 0.01909 -0.0789 0.0133 1.0000
11.750 1.5674 0.02622 0.02009 -0.0773 0.0129 1.0000
12.000 1.5758 0.02746 0.02138 -0.0754 0.0124 1.0000
12.250 1.5734 0.02961 0.02362 -0.0725 0.0118 1.0000
12.500 1.5804 0.03108 0.02518 -0.0708 0.0116 1.0000
12.750 1.5907 0.03231 0.02649 -0.0694 0.0113 1.0000
13.000 1.5995 0.03371 0.02796 -0.0681 0.0109 1.0000
13.250 1.6073 0.03523 0.02955 -0.0667 0.0106 1.0000
13.500 1.6135 0.03694 0.03133 -0.0654 0.0103 1.0000
13.750 1.6192 0.03874 0.03320 -0.0642 0.0100 1.0000
14.000 1.6236 0.04074 0.03527 -0.0631 0.0097 1.0000
14.250 1.6251 0.04308 0.03769 -0.0620 0.0095 1.0000
14.500 1.6215 0.04603 0.04073 -0.0608 0.0092 1.0000
14.750 1.6114 0.04985 0.04468 -0.0597 0.0090 1.0000
15.000 1.6052 0.05337 0.04833 -0.0589 0.0088 1.0000
15.250 1.6071 0.05605 0.05110 -0.0585 0.0087 1.0000
15.500 1.6073 0.05902 0.05418 -0.0582 0.0086 1.0000
15.750 1.6057 0.06226 0.05753 -0.0581 0.0085 1.0000
16.000 1.6036 0.06564 0.06101 -0.0580 0.0084 1.0000
16.250 1.6006 0.06919 0.06467 -0.0582 0.0082 1.0000
16.500 1.5965 0.07297 0.06856 -0.0584 0.0081 1.0000
16.750 1.5917 0.07693 0.07263 -0.0589 0.0080 1.0000
17.000 1.5864 0.08106 0.07687 -0.0595 0.0078 1.0000
17.250 1.5806 0.08529 0.08121 -0.0602 0.0077 1.0000
17.500 1.5744 0.08968 0.08570 -0.0612 0.0076 1.0000
17.750 1.5680 0.09419 0.09031 -0.0623 0.0075 1.0000
18.000 1.5616 0.09881 0.09503 -0.0635 0.0074 1.0000
18.250 1.5544 0.10359 0.09991 -0.0650 0.0073 1.0000
18.500 1.5459 0.10862 0.10503 -0.0666 0.0072 1.0000
18.750 1.5374 0.11375 0.11026 -0.0684 0.0071 1.0000
19.000 1.5276 0.11915 0.11576 -0.0705 0.0070 1.0000
19.250 1.5167 0.12483 0.12154 -0.0728 0.0069 1.0000
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