GOE 434 AIRFOIL (goe434-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 434 AIRFOIL (goe434-il) Reynolds number: 200,000 Max Cl/Cd: 65.26 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe434-il-200000.txt Download as CSV file: xf-goe434-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 434 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7248 0.05909 0.05352 -0.1039 0.9938 0.0970
-14.000 -0.7370 0.05178 0.04587 -0.1137 0.9856 0.0979
-13.750 -0.7335 0.04616 0.03993 -0.1228 0.9778 0.0989
-13.500 -0.7282 0.04161 0.03505 -0.1305 0.9646 0.0999
-13.250 -0.6851 0.04078 0.03437 -0.1315 0.9600 0.1015
-13.000 -0.6590 0.03953 0.03316 -0.1327 0.9458 0.1029
-12.750 -0.6440 0.03774 0.03130 -0.1340 0.9278 0.1043
-12.500 -0.6363 0.03582 0.02924 -0.1346 0.9071 0.1055
-12.250 -0.6299 0.03399 0.02723 -0.1349 0.8865 0.1066
-12.000 -0.6249 0.03234 0.02535 -0.1351 0.8672 0.1076
-11.750 -0.6086 0.03121 0.02415 -0.1346 0.8521 0.1089
-11.500 -0.5875 0.03052 0.02346 -0.1338 0.8394 0.1104
-11.250 -0.5688 0.02967 0.02257 -0.1340 0.8255 0.1120
-11.000 -0.5501 0.02869 0.02143 -0.1345 0.8146 0.1137
-10.750 -0.5315 0.02772 0.02033 -0.1351 0.8031 0.1155
-10.500 -0.5111 0.02685 0.01931 -0.1353 0.7941 0.1171
-10.250 -0.4881 0.02626 0.01875 -0.1352 0.7865 0.1190
-10.000 -0.4657 0.02565 0.01815 -0.1354 0.7785 0.1211
-9.750 -0.4428 0.02501 0.01742 -0.1357 0.7716 0.1235
-9.500 -0.4189 0.02438 0.01660 -0.1361 0.7656 0.1259
-9.250 -0.3953 0.02382 0.01614 -0.1361 0.7598 0.1282
-9.000 -0.3709 0.02332 0.01565 -0.1364 0.7536 0.1310
-8.750 -0.3458 0.02281 0.01507 -0.1367 0.7481 0.1345
-8.500 -0.3206 0.02228 0.01451 -0.1369 0.7435 0.1379
-8.250 -0.2943 0.02188 0.01409 -0.1372 0.7392 0.1418
-8.000 -0.2683 0.02147 0.01362 -0.1375 0.7350 0.1467
-7.750 -0.2434 0.02093 0.01319 -0.1378 0.7303 0.1520
-7.500 -0.2167 0.02049 0.01269 -0.1381 0.7257 0.1596
-7.250 -0.1908 0.01989 0.01218 -0.1385 0.7217 0.1689
-7.000 -0.1641 0.01931 0.01166 -0.1390 0.7181 0.1819
-6.750 -0.1364 0.01889 0.01127 -0.1396 0.7145 0.1983
-6.500 -0.1089 0.01864 0.01108 -0.1401 0.7108 0.2150
-6.250 -0.0811 0.01852 0.01104 -0.1404 0.7069 0.2301
-6.000 -0.0524 0.01852 0.01106 -0.1406 0.7031 0.2433
-5.750 -0.0234 0.01856 0.01114 -0.1408 0.6992 0.2543
-5.500 0.0063 0.01860 0.01113 -0.1411 0.6956 0.2651
-5.250 0.0366 0.01873 0.01118 -0.1414 0.6923 0.2756
-5.000 0.0664 0.01897 0.01139 -0.1416 0.6888 0.2841
-4.750 0.0942 0.01912 0.01157 -0.1415 0.6854 0.2932
-4.500 0.1221 0.01922 0.01169 -0.1415 0.6816 0.3015
-4.250 0.1506 0.01942 0.01194 -0.1414 0.6777 0.3091
-4.000 0.1803 0.01957 0.01196 -0.1416 0.6740 0.3180
-3.750 0.2094 0.01961 0.01208 -0.1416 0.6708 0.3248
-3.500 0.2395 0.01981 0.01226 -0.1417 0.6678 0.3319
-3.250 0.2700 0.02013 0.01243 -0.1420 0.6645 0.3396
-3.000 0.2965 0.02013 0.01252 -0.1418 0.6610 0.3457
-2.750 0.3232 0.02032 0.01282 -0.1414 0.6571 0.3516
-2.500 0.3511 0.02050 0.01301 -0.1413 0.6533 0.3585
-2.250 0.3803 0.02065 0.01306 -0.1415 0.6497 0.3647
-2.000 0.4095 0.02053 0.01295 -0.1416 0.6464 0.3702
-1.750 0.4397 0.02061 0.01305 -0.1417 0.6431 0.3755
-1.500 0.4700 0.02094 0.01331 -0.1419 0.6397 0.3817
-1.250 0.4959 0.02111 0.01350 -0.1416 0.6360 0.3880
-1.000 0.5221 0.02117 0.01359 -0.1414 0.6320 0.3936
-0.750 0.5487 0.02126 0.01377 -0.1411 0.6279 0.3988
-0.500 0.5773 0.02130 0.01383 -0.1410 0.6239 0.4039
-0.250 0.6084 0.02123 0.01368 -0.1413 0.6200 0.4091
0.000 0.6412 0.02128 0.01357 -0.1419 0.6159 0.4142
0.250 0.6665 0.02133 0.01365 -0.1415 0.6108 0.4185
0.500 0.6914 0.02129 0.01372 -0.1409 0.6055 0.4234
0.750 0.7190 0.02130 0.01377 -0.1407 0.6009 0.4286
1.000 0.7496 0.02122 0.01365 -0.1409 0.5968 0.4342
1.250 0.7826 0.02115 0.01345 -0.1414 0.5929 0.4399
1.500 0.8107 0.02130 0.01355 -0.1414 0.5883 0.4445
1.750 0.8336 0.02126 0.01366 -0.1406 0.5827 0.4496
2.000 0.8604 0.02124 0.01369 -0.1403 0.5777 0.4551
2.250 0.8908 0.02112 0.01355 -0.1404 0.5733 0.4613
2.500 0.9240 0.02100 0.01331 -0.1410 0.5695 0.4673
2.750 0.9512 0.02105 0.01335 -0.1409 0.5646 0.4725
3.000 0.9735 0.02099 0.01344 -0.1399 0.5582 0.4781
3.250 1.0018 0.02083 0.01328 -0.1397 0.5528 0.4845
3.500 1.0339 0.02062 0.01300 -0.1401 0.5484 0.4922
3.750 1.0640 0.02063 0.01295 -0.1403 0.5443 0.5000
4.000 1.0838 0.02074 0.01326 -0.1389 0.5382 0.5076
4.250 1.1100 0.02071 0.01327 -0.1385 0.5328 0.5169
4.500 1.1406 0.02053 0.01302 -0.1387 0.5281 0.5271
4.750 1.1682 0.02046 0.01301 -0.1384 0.5232 0.5370
5.000 1.1877 0.02060 0.01326 -0.1370 0.5163 0.5483
5.250 1.2137 0.02046 0.01317 -0.1364 0.5104 0.5598
5.500 1.2448 0.02030 0.01293 -0.1367 0.5055 0.5745
5.750 1.2597 0.02051 0.01336 -0.1345 0.4978 0.5868
6.000 1.2830 0.02049 0.01334 -0.1336 0.4910 0.6031
6.250 1.3059 0.02046 0.01337 -0.1326 0.4841 0.6184
6.500 1.3212 0.02061 0.01364 -0.1305 0.4753 0.6341
6.750 1.3436 0.02059 0.01357 -0.1293 0.4672 0.6525
7.000 1.3515 0.02084 0.01397 -0.1260 0.4569 0.6680
7.250 1.3663 0.02105 0.01420 -0.1238 0.4467 0.6861
7.500 1.3777 0.02146 0.01462 -0.1213 0.4348 0.7055
7.750 1.3865 0.02205 0.01526 -0.1186 0.4220 0.7260
8.000 1.3947 0.02270 0.01592 -0.1159 0.4088 0.7472
8.250 1.4006 0.02351 0.01671 -0.1131 0.3941 0.7699
8.500 1.4022 0.02461 0.01782 -0.1101 0.3777 0.7943
8.750 1.4013 0.02592 0.01916 -0.1070 0.3602 0.8251
9.000 1.3960 0.02724 0.02058 -0.1033 0.3431 0.8943
9.250 1.3921 0.02904 0.02229 -0.1008 0.3264 1.0000
9.500 1.3928 0.03107 0.02419 -0.0991 0.3117 1.0000
9.750 1.3947 0.03305 0.02606 -0.0976 0.2997 1.0000
10.000 1.3968 0.03503 0.02789 -0.0960 0.2900 1.0000
10.250 1.4034 0.03678 0.02961 -0.0949 0.2814 1.0000
10.500 1.4090 0.03855 0.03123 -0.0937 0.2746 1.0000
10.750 1.4186 0.04008 0.03275 -0.0927 0.2687 1.0000
11.000 1.4282 0.04161 0.03425 -0.0918 0.2634 1.0000
11.250 1.4400 0.04291 0.03542 -0.0908 0.2589 1.0000
11.500 1.4538 0.04408 0.03655 -0.0900 0.2549 1.0000
11.750 1.4652 0.04551 0.03802 -0.0893 0.2511 1.0000
12.000 1.4769 0.04690 0.03940 -0.0885 0.2474 1.0000
12.250 1.4909 0.04803 0.04045 -0.0877 0.2438 1.0000
12.500 1.5097 0.04871 0.04101 -0.0869 0.2400 1.0000
12.750 1.5168 0.05058 0.04298 -0.0863 0.2369 1.0000
13.000 1.5268 0.05217 0.04461 -0.0856 0.2336 1.0000
13.250 1.5386 0.05357 0.04602 -0.0849 0.2306 1.0000
13.500 1.5528 0.05470 0.04711 -0.0843 0.2276 1.0000
13.750 1.5779 0.05478 0.04702 -0.0835 0.2241 1.0000
14.000 1.5800 0.05715 0.04954 -0.0829 0.2217 1.0000
14.250 1.5864 0.05913 0.05162 -0.0824 0.2190 1.0000
14.500 1.5954 0.06082 0.05336 -0.0818 0.2163 1.0000
14.750 1.6060 0.06235 0.05490 -0.0813 0.2137 1.0000
15.000 1.6202 0.06348 0.05599 -0.0807 0.2110 1.0000
15.250 1.6473 0.06333 0.05571 -0.0800 0.2080 1.0000
15.500 1.6440 0.06631 0.05887 -0.0796 0.2059 1.0000
15.750 1.6444 0.06894 0.06163 -0.0792 0.2034 1.0000
16.000 1.6479 0.07126 0.06403 -0.0789 0.2006 1.0000
16.250 1.6552 0.07314 0.06594 -0.0785 0.1979 1.0000
16.500 1.6680 0.07438 0.06714 -0.0781 0.1952 1.0000
16.750 1.6888 0.07475 0.06743 -0.0774 0.1921 1.0000
17.000 1.6764 0.07890 0.07180 -0.0774 0.1897 1.0000
17.250 1.6703 0.08242 0.07547 -0.0775 0.1866 1.0000
17.500 1.6722 0.08499 0.07809 -0.0775 0.1834 1.0000
17.750 1.6822 0.08652 0.07958 -0.0773 0.1804 1.0000
18.000 1.6943 0.08777 0.08078 -0.0769 0.1771 1.0000
18.250 1.6739 0.09325 0.08651 -0.0777 0.1739 1.0000
18.500 1.6680 0.09696 0.09032 -0.0782 0.1702 1.0000
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Polar data table (+)
Polar graphs
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