GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Reynolds number: 500,000 Max Cl/Cd: 97.13 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe331-il-500000.txt Download as CSV file: xf-goe331-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 331 (PFALZ 60) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0643 0.09055 0.08816 -0.0748 0.9249 0.0197
-8.500 -0.0577 0.08813 0.08569 -0.0753 0.9067 0.0199
-8.250 -0.0506 0.08566 0.08317 -0.0761 0.8899 0.0203
-8.000 -0.0429 0.08315 0.08059 -0.0771 0.8753 0.0206
-7.750 -0.0344 0.08060 0.07796 -0.0786 0.8627 0.0211
-7.500 -0.0252 0.07804 0.07534 -0.0811 0.8510 0.0216
-7.250 -0.0093 0.07498 0.07220 -0.0893 0.8407 0.0218
-6.750 0.0264 0.06802 0.06510 -0.0992 0.8243 0.0219
-6.500 0.0388 0.06533 0.06238 -0.0986 0.8170 0.0220
-6.250 0.0544 0.06271 0.05970 -0.0999 0.8106 0.0222
-6.000 0.0729 0.06004 0.05700 -0.1024 0.8039 0.0224
-5.750 0.0936 0.05736 0.05425 -0.1054 0.7979 0.0227
-5.500 0.1163 0.05463 0.05146 -0.1088 0.7920 0.0230
-5.250 0.1406 0.05186 0.04864 -0.1122 0.7857 0.0236
-5.000 0.1678 0.04902 0.04568 -0.1159 0.7802 0.0245
-4.750 0.2156 0.04518 0.04154 -0.1242 0.7750 0.0251
-4.500 0.2381 0.04218 0.03848 -0.1258 0.7692 0.0252
-4.250 0.2577 0.03994 0.03619 -0.1264 0.7638 0.0254
-4.000 0.2803 0.03790 0.03410 -0.1274 0.7582 0.0256
-3.750 0.3053 0.03589 0.03203 -0.1286 0.7521 0.0259
-3.500 0.3321 0.03394 0.02996 -0.1299 0.7468 0.0264
-3.250 0.3601 0.03204 0.02792 -0.1311 0.7415 0.0272
-3.000 0.3989 0.03002 0.02556 -0.1324 0.7353 0.0287
-2.750 0.4256 0.02766 0.02300 -0.1330 0.7292 0.0289
-2.500 0.4494 0.02598 0.02130 -0.1336 0.7229 0.0292
-2.250 0.4749 0.02459 0.01984 -0.1340 0.7162 0.0296
-2.000 0.5019 0.02331 0.01841 -0.1344 0.7098 0.0304
-1.750 0.5301 0.02200 0.01698 -0.1345 0.7024 0.0316
-1.500 0.5621 0.02057 0.01514 -0.1342 0.6958 0.0332
-1.250 0.5877 0.01936 0.01393 -0.1346 0.6885 0.0337
-1.000 0.6144 0.01846 0.01293 -0.1347 0.6808 0.0346
-0.750 0.6425 0.01760 0.01193 -0.1346 0.6737 0.0362
-0.500 0.6717 0.01664 0.01068 -0.1343 0.6657 0.0383
-0.250 0.6983 0.01583 0.00983 -0.1344 0.6576 0.0393
0.000 0.7258 0.01530 0.00916 -0.1342 0.6480 0.0419
0.250 0.7533 0.01455 0.00826 -0.1341 0.6382 0.0450
0.750 0.8069 0.01361 0.00713 -0.1337 0.6159 0.0536
1.000 0.8336 0.01325 0.00665 -0.1335 0.6039 0.0611
1.250 0.8597 0.01296 0.00627 -0.1332 0.5908 0.0707
1.500 0.8853 0.01267 0.00593 -0.1330 0.5764 0.0834
1.750 0.9104 0.01245 0.00566 -0.1327 0.5603 0.1003
2.750 1.0107 0.01174 0.00428 -0.1288 0.4743 0.0481
3.000 1.0330 0.01184 0.00420 -0.1277 0.4424 0.0454
3.250 1.0543 0.01210 0.00428 -0.1266 0.4085 0.0449
3.500 1.0757 0.01239 0.00443 -0.1255 0.3833 0.0465
3.750 1.0983 0.01264 0.00457 -0.1247 0.3669 0.0462
4.000 1.1215 0.01287 0.00473 -0.1239 0.3555 0.0461
4.250 1.1452 0.01308 0.00489 -0.1233 0.3470 0.0467
4.500 1.1683 0.01334 0.00509 -0.1225 0.3396 0.0482
4.750 1.1915 0.01359 0.00531 -0.1218 0.3334 0.0504
5.000 1.2155 0.01379 0.00553 -0.1212 0.3280 0.0630
5.250 1.2355 0.01272 0.00601 -0.1201 0.3233 1.0000
5.500 1.2573 0.01310 0.00632 -0.1192 0.3187 1.0000
5.750 1.2814 0.01332 0.00655 -0.1187 0.3153 1.0000
6.000 1.3045 0.01360 0.00681 -0.1180 0.3116 1.0000
6.250 1.3266 0.01393 0.00711 -0.1171 0.3081 1.0000
6.500 1.3472 0.01434 0.00748 -0.1160 0.3042 1.0000
6.750 1.3691 0.01465 0.00780 -0.1151 0.3007 1.0000
7.000 1.3907 0.01488 0.00807 -0.1142 0.2971 1.0000
7.250 1.4112 0.01518 0.00837 -0.1131 0.2935 1.0000
7.500 1.4308 0.01555 0.00874 -0.1119 0.2904 1.0000
7.750 1.4496 0.01604 0.00920 -0.1105 0.2871 1.0000
8.000 1.4703 0.01637 0.00957 -0.1095 0.2846 1.0000
8.250 1.4910 0.01667 0.00994 -0.1086 0.2820 1.0000
8.500 1.5112 0.01700 0.01032 -0.1075 0.2792 1.0000
8.750 1.5307 0.01738 0.01072 -0.1064 0.2762 1.0000
9.000 1.5489 0.01784 0.01118 -0.1052 0.2730 1.0000
9.250 1.5670 0.01837 0.01172 -0.1039 0.2694 1.0000
9.500 1.5863 0.01868 0.01213 -0.1029 0.2662 1.0000
9.750 1.6048 0.01906 0.01256 -0.1018 0.2623 1.0000
10.000 1.6220 0.01954 0.01307 -0.1005 0.2585 1.0000
10.250 1.6372 0.02022 0.01373 -0.0990 0.2543 1.0000
10.500 1.6560 0.02059 0.01422 -0.0981 0.2512 1.0000
10.750 1.6736 0.02106 0.01476 -0.0970 0.2467 1.0000
11.000 1.6884 0.02171 0.01542 -0.0956 0.2417 1.0000
11.250 1.7038 0.02235 0.01613 -0.0944 0.2370 1.0000
11.500 1.7209 0.02291 0.01677 -0.0934 0.2317 1.0000
11.750 1.7340 0.02374 0.01761 -0.0921 0.2260 1.0000
12.000 1.7496 0.02444 0.01839 -0.0910 0.2201 1.0000
12.250 1.7629 0.02531 0.01930 -0.0898 0.2131 1.0000
12.500 1.7758 0.02624 0.02028 -0.0887 0.2049 1.0000
12.750 1.7851 0.02747 0.02150 -0.0872 0.1951 1.0000
13.000 1.7942 0.02876 0.02280 -0.0859 0.1826 1.0000
13.250 1.7986 0.03044 0.02443 -0.0842 0.1648 1.0000
13.500 1.7936 0.03295 0.02680 -0.0819 0.1414 1.0000
13.750 1.7851 0.03584 0.02958 -0.0795 0.1213 1.0000
14.000 1.7753 0.03897 0.03263 -0.0773 0.1045 1.0000
14.250 1.7614 0.04265 0.03621 -0.0751 0.0824 1.0000
14.500 1.7389 0.04736 0.04077 -0.0730 0.0569 1.0000
14.750 1.7195 0.05207 0.04543 -0.0715 0.0432 1.0000
15.000 1.7053 0.05642 0.04982 -0.0704 0.0359 1.0000
15.250 1.6934 0.06073 0.05420 -0.0698 0.0319 1.0000
15.500 1.6836 0.06494 0.05850 -0.0695 0.0294 1.0000
15.750 1.6707 0.06968 0.06334 -0.0694 0.0276 1.0000
16.000 1.6617 0.07404 0.06782 -0.0695 0.0265 1.0000
16.250 1.6514 0.07870 0.07260 -0.0698 0.0255 1.0000
16.500 1.6390 0.08377 0.07779 -0.0703 0.0246 1.0000
16.750 1.6239 0.08930 0.08344 -0.0711 0.0240 1.0000
17.000 1.6066 0.09530 0.08957 -0.0722 0.0234 1.0000
17.250 1.5873 0.10177 0.09617 -0.0736 0.0229 1.0000
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