GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 567 AIRFOIL (goe567-il) Reynolds number: 100,000 Max Cl/Cd: 55.96 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe567-il-100000-n5.txt Download as CSV file: xf-goe567-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 567 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2969 0.09411 0.08898 -0.0656 0.9837 0.0711
-10.000 -0.2993 0.08668 0.08153 -0.0726 0.9744 0.0728
-9.750 -0.4365 0.05051 0.04498 -0.1128 0.9387 0.0746
-9.500 -0.4325 0.04363 0.03757 -0.1226 0.9266 0.0763
-9.250 -0.4133 0.04189 0.03576 -0.1238 0.9156 0.0778
-9.000 -0.3904 0.03926 0.03288 -0.1270 0.9079 0.0794
-8.750 -0.3695 0.03701 0.03036 -0.1290 0.8981 0.0815
-8.500 -0.3465 0.03462 0.02757 -0.1313 0.8898 0.0840
-8.250 -0.3228 0.03235 0.02482 -0.1332 0.8814 0.0862
-8.000 -0.2968 0.03050 0.02248 -0.1347 0.8736 0.0879
-7.750 -0.2700 0.02909 0.02105 -0.1355 0.8660 0.0899
-7.500 -0.2394 0.02803 0.01988 -0.1367 0.8601 0.0923
-7.250 -0.2144 0.02707 0.01876 -0.1369 0.8514 0.0946
-7.000 -0.1832 0.02592 0.01736 -0.1381 0.8456 0.0970
-6.750 -0.1582 0.02505 0.01626 -0.1380 0.8371 0.0993
-6.500 -0.1283 0.02416 0.01512 -0.1388 0.8308 0.1020
-6.250 -0.1016 0.02340 0.01437 -0.1389 0.8236 0.1045
-6.000 -0.0740 0.02276 0.01367 -0.1391 0.8164 0.1072
-5.750 -0.0436 0.02210 0.01289 -0.1397 0.8109 0.1102
-5.500 -0.0186 0.02164 0.01231 -0.1393 0.8027 0.1136
-5.250 0.0107 0.02107 0.01164 -0.1397 0.7967 0.1172
-5.000 0.0369 0.02063 0.01120 -0.1395 0.7898 0.1208
-4.750 0.0640 0.02023 0.01074 -0.1395 0.7829 0.1248
-4.250 0.1184 0.01951 0.00993 -0.1394 0.7698 0.1357
-4.000 0.1470 0.01918 0.00953 -0.1396 0.7637 0.1436
-3.750 0.1745 0.01884 0.00920 -0.1397 0.7575 0.1526
-3.500 0.2007 0.01856 0.00893 -0.1395 0.7504 0.1652
-3.250 0.2299 0.01821 0.00862 -0.1399 0.7449 0.1877
-3.000 0.2559 0.01797 0.00848 -0.1397 0.7381 0.2190
-2.750 0.2830 0.01779 0.00839 -0.1397 0.7315 0.2548
-2.500 0.3128 0.01766 0.00826 -0.1399 0.7265 0.2884
-2.250 0.3375 0.01769 0.00834 -0.1394 0.7190 0.3158
-2.000 0.3653 0.01769 0.00833 -0.1393 0.7129 0.3429
-1.750 0.3940 0.01772 0.00832 -0.1393 0.7075 0.3663
-1.500 0.4187 0.01782 0.00846 -0.1387 0.7002 0.3868
-1.250 0.4469 0.01788 0.00848 -0.1385 0.6945 0.4098
-1.000 0.4738 0.01800 0.00858 -0.1382 0.6886 0.4330
-0.750 0.4990 0.01813 0.00875 -0.1376 0.6817 0.4524
-0.500 0.5273 0.01819 0.00878 -0.1375 0.6765 0.4709
-0.250 0.5527 0.01831 0.00890 -0.1370 0.6701 0.4864
0.000 0.5786 0.01839 0.00898 -0.1365 0.6636 0.4995
0.250 0.6072 0.01840 0.00895 -0.1365 0.6587 0.5119
0.500 0.6313 0.01854 0.00911 -0.1358 0.6520 0.5241
0.750 0.6577 0.01862 0.00918 -0.1355 0.6460 0.5374
1.000 0.6865 0.01862 0.00914 -0.1354 0.6414 0.5503
1.250 0.7092 0.01878 0.00938 -0.1345 0.6343 0.5624
1.500 0.7357 0.01886 0.00946 -0.1342 0.6288 0.5756
1.750 0.7649 0.01888 0.00944 -0.1342 0.6243 0.5897
2.000 0.7874 0.01908 0.00973 -0.1334 0.6172 0.6036
2.250 0.8142 0.01914 0.00981 -0.1331 0.6118 0.6180
2.500 0.8423 0.01918 0.00985 -0.1330 0.6074 0.6338
2.750 0.8645 0.01938 0.01018 -0.1320 0.6006 0.6502
3.000 0.8910 0.01941 0.01026 -0.1317 0.5951 0.6700
3.250 0.9170 0.01943 0.01036 -0.1312 0.5900 0.6935
3.500 0.9380 0.01951 0.01063 -0.1299 0.5828 0.7260
3.750 0.9608 0.01920 0.01060 -0.1284 0.5772 0.8116
4.000 0.9871 0.01932 0.01080 -0.1282 0.5695 1.0000
4.250 1.0135 0.01950 0.01091 -0.1280 0.5626 1.0000
4.500 1.0389 0.01972 0.01109 -0.1276 0.5559 1.0000
4.750 1.0622 0.02001 0.01139 -0.1268 0.5486 1.0000
5.000 1.0906 0.02016 0.01146 -0.1268 0.5432 1.0000
5.250 1.1108 0.02058 0.01195 -0.1257 0.5362 1.0000
5.500 1.1357 0.02085 0.01222 -0.1252 0.5301 1.0000
5.750 1.1605 0.02111 0.01247 -0.1247 0.5241 1.0000
6.000 1.1806 0.02146 0.01287 -0.1234 0.5159 1.0000
6.250 1.2049 0.02164 0.01302 -0.1227 0.5080 1.0000
6.500 1.2230 0.02197 0.01341 -0.1211 0.4981 1.0000
6.750 1.2430 0.02225 0.01369 -0.1197 0.4889 1.0000
7.000 1.2625 0.02256 0.01402 -0.1183 0.4799 1.0000
7.250 1.2806 0.02296 0.01449 -0.1168 0.4717 1.0000
7.500 1.2992 0.02332 0.01490 -0.1153 0.4636 1.0000
7.750 1.3165 0.02376 0.01540 -0.1136 0.4560 1.0000
8.000 1.3320 0.02420 0.01592 -0.1117 0.4481 1.0000
8.250 1.3459 0.02466 0.01644 -0.1095 0.4397 1.0000
8.500 1.3582 0.02513 0.01695 -0.1071 0.4299 1.0000
8.750 1.3667 0.02578 0.01769 -0.1043 0.4196 1.0000
9.000 1.3780 0.02636 0.01829 -0.1020 0.4094 1.0000
9.250 1.3857 0.02713 0.01914 -0.0993 0.3985 1.0000
9.500 1.3917 0.02803 0.02013 -0.0966 0.3868 1.0000
9.750 1.3983 0.02898 0.02112 -0.0941 0.3750 1.0000
10.000 1.4042 0.03002 0.02220 -0.0917 0.3628 1.0000
10.250 1.4078 0.03129 0.02352 -0.0893 0.3493 1.0000
10.500 1.4105 0.03273 0.02502 -0.0870 0.3352 1.0000
10.750 1.4126 0.03431 0.02665 -0.0849 0.3207 1.0000
11.000 1.4138 0.03607 0.02844 -0.0828 0.3053 1.0000
11.250 1.4128 0.03808 0.03045 -0.0809 0.2881 1.0000
11.500 1.4092 0.04042 0.03275 -0.0790 0.2692 1.0000
11.750 1.4045 0.04302 0.03531 -0.0773 0.2501 1.0000
12.000 1.3992 0.04580 0.03806 -0.0759 0.2325 1.0000
12.250 1.3932 0.04880 0.04103 -0.0746 0.2157 1.0000
12.500 1.3864 0.05201 0.04423 -0.0736 0.1995 1.0000
12.750 1.3793 0.05543 0.04761 -0.0727 0.1837 1.0000
13.000 1.3728 0.05893 0.05112 -0.0721 0.1697 1.0000
13.250 1.3670 0.06247 0.05465 -0.0717 0.1584 1.0000
13.500 1.3611 0.06615 0.05831 -0.0714 0.1490 1.0000
13.750 1.3571 0.06970 0.06187 -0.0713 0.1409 1.0000
14.000 1.3539 0.07319 0.06537 -0.0712 0.1342 1.0000
14.250 1.3520 0.07660 0.06881 -0.0712 0.1274 1.0000
14.500 1.3499 0.08004 0.07222 -0.0713 0.1215 1.0000
14.750 1.3519 0.08305 0.07535 -0.0714 0.1154 1.0000
15.000 1.3513 0.08636 0.07865 -0.0715 0.1097 1.0000
15.250 1.3538 0.08936 0.08175 -0.0717 0.1041 1.0000
15.500 1.3552 0.09261 0.08510 -0.0722 0.0984 1.0000
15.750 1.3557 0.09593 0.08842 -0.0727 0.0937 1.0000
16.000 1.3589 0.09909 0.09179 -0.0732 0.0880 1.0000
16.250 1.3586 0.10274 0.09552 -0.0741 0.0833 1.0000
16.500 1.3606 0.10609 0.09901 -0.0750 0.0782 1.0000
16.750 1.3595 0.10999 0.10298 -0.0762 0.0740 1.0000
17.000 1.3593 0.11373 0.10679 -0.0773 0.0703 1.0000
17.250 1.3579 0.11772 0.11084 -0.0787 0.0671 1.0000
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Polar data table (+)
Polar graphs
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