GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 366 AIRFOIL (goe366-il) Reynolds number: 100,000 Max Cl/Cd: 51.73 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe366-il-100000.txt Download as CSV file: xf-goe366-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 366 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.0892 0.10551 0.10095 -0.0720 0.9289 0.0623
-7.000 -0.1007 0.10503 0.10051 -0.0722 0.9172 0.0628
-6.750 -0.1014 0.10409 0.09957 -0.0783 0.9056 0.0632
-6.500 -0.0827 0.09922 0.09472 -0.0776 0.9012 0.0640
-6.250 -0.0551 0.09476 0.09026 -0.0790 0.8981 0.0656
-6.000 -0.0538 0.09293 0.08844 -0.0783 0.8881 0.0668
-5.750 -0.0314 0.08963 0.08511 -0.0829 0.8818 0.0692
-5.500 -0.0231 0.08787 0.08332 -0.0867 0.8712 0.0716
-5.250 0.0069 0.08417 0.07952 -0.0960 0.8640 0.0736
-5.000 0.0366 0.07972 0.07509 -0.0968 0.8616 0.0761
-4.750 0.0358 0.07827 0.07366 -0.0949 0.8489 0.0777
-4.500 0.1026 0.07524 0.07018 -0.1128 0.8443 0.0843
-3.750 0.1968 0.06523 0.05989 -0.1229 0.8260 0.0973
-3.250 0.2369 0.05853 0.05334 -0.1226 0.8111 0.1042
-3.000 0.2616 0.05736 0.05186 -0.1252 0.7982 0.1124
-2.750 0.3008 0.05325 0.04781 -0.1281 0.7957 0.1191
-2.500 0.3395 0.05045 0.04485 -0.1319 0.7898 0.1318
-2.250 0.3698 0.04838 0.04263 -0.1337 0.7808 0.1472
-2.000 0.4140 0.04518 0.03934 -0.1374 0.7777 0.1669
-1.750 0.4345 0.04365 0.03774 -0.1371 0.7664 0.1844
-1.500 0.4766 0.04090 0.03486 -0.1402 0.7620 0.2180
-1.250 0.5184 0.03801 0.03191 -0.1431 0.7590 0.2699
-0.500 0.5815 0.03266 0.02673 -0.1392 0.7292 0.4201
-0.250 0.6248 0.03033 0.02428 -0.1412 0.7245 0.4681
0.000 0.6480 0.02925 0.02315 -0.1405 0.7116 0.4846
0.250 0.7375 0.02845 0.02096 -0.1512 0.7062 0.2990
0.500 0.7740 0.02844 0.02017 -0.1500 0.6932 0.1735
0.750 0.8104 0.02741 0.01868 -0.1499 0.6845 0.1355
1.000 0.8417 0.02662 0.01760 -0.1493 0.6745 0.1190
1.250 0.8689 0.02632 0.01702 -0.1483 0.6640 0.1093
1.500 0.9022 0.02535 0.01592 -0.1486 0.6557 0.1041
1.750 0.9249 0.02514 0.01562 -0.1473 0.6448 0.1013
2.000 0.9595 0.02439 0.01474 -0.1478 0.6375 0.1028
2.250 0.9787 0.02435 0.01473 -0.1461 0.6264 0.1035
2.500 1.0124 0.02377 0.01399 -0.1465 0.6195 0.1038
2.750 1.0321 0.02393 0.01414 -0.1450 0.6089 0.1051
3.000 1.0638 0.02372 0.01374 -0.1453 0.6015 0.1086
3.250 1.0868 0.02387 0.01383 -0.1444 0.5920 0.1151
3.500 1.1178 0.02376 0.01367 -0.1447 0.5846 0.1408
3.750 1.1361 0.02262 0.01405 -0.1428 0.5761 1.0000
4.000 1.1700 0.02275 0.01380 -0.1435 0.5699 1.0000
4.250 1.1874 0.02343 0.01443 -0.1419 0.5610 1.0000
4.500 1.2209 0.02360 0.01432 -0.1427 0.5547 1.0000
4.750 1.2381 0.02435 0.01508 -0.1412 0.5464 1.0000
5.000 1.2669 0.02471 0.01528 -0.1414 0.5397 1.0000
5.250 1.2908 0.02536 0.01587 -0.1410 0.5333 1.0000
5.500 1.3107 0.02608 0.01660 -0.1399 0.5263 1.0000
5.750 1.3439 0.02643 0.01677 -0.1409 0.5209 1.0000
6.000 1.3582 0.02739 0.01783 -0.1391 0.5140 1.0000
6.250 1.3804 0.02806 0.01851 -0.1384 0.5077 1.0000
6.500 1.4147 0.02850 0.01878 -0.1397 0.5030 1.0000
6.750 1.4239 0.02971 0.02017 -0.1372 0.4970 1.0000
7.000 1.4426 0.03058 0.02110 -0.1361 0.4913 1.0000
7.250 1.4742 0.03105 0.02148 -0.1369 0.4866 1.0000
7.500 1.4872 0.03223 0.02278 -0.1351 0.4812 1.0000
7.750 1.4973 0.03346 0.02415 -0.1328 0.4757 1.0000
8.000 1.5222 0.03420 0.02491 -0.1327 0.4713 1.0000
8.250 1.5591 0.03469 0.02530 -0.1345 0.4675 1.0000
8.500 1.5458 0.03682 0.02775 -0.1289 0.4618 1.0000
8.750 1.5567 0.03805 0.02909 -0.1269 0.4567 1.0000
9.000 1.5923 0.03826 0.02926 -0.1283 0.4522 1.0000
9.250 1.5987 0.03979 0.03092 -0.1257 0.4474 1.0000
9.500 1.5807 0.04219 0.03355 -0.1199 0.4416 1.0000
9.750 1.6191 0.04190 0.03321 -0.1213 0.4361 1.0000
10.000 1.6445 0.04245 0.03380 -0.1212 0.4311 1.0000
10.250 1.5727 0.04746 0.03913 -0.1092 0.4257 1.0000
10.500 1.6047 0.04728 0.03899 -0.1096 0.4205 1.0000
10.750 1.6871 0.04494 0.03650 -0.1163 0.4149 1.0000
11.250 1.4448 0.06670 0.05887 -0.0920 0.4004 1.0000
11.500 1.7088 0.04811 0.03996 -0.1090 0.3994 1.0000
11.750 1.0575 0.12940 0.12188 -0.0985 0.3577 1.0000
12.000 1.0860 0.12869 0.12119 -0.0974 0.3526 1.0000
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Polar data table (+)
Polar graphs
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