GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 675 AIRFOIL (goe675-il) Reynolds number: 100,000 Max Cl/Cd: 52.23 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe675-il-100000-n5.txt Download as CSV file: xf-goe675-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 675 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1023 0.09837 0.09261 -0.0945 0.9437 0.0594
-9.500 -0.0931 0.09427 0.08850 -0.0982 0.9406 0.0597
-9.250 -0.0921 0.09091 0.08514 -0.0997 0.9339 0.0596
-9.000 -0.0889 0.08706 0.08129 -0.1022 0.9283 0.0594
-8.750 -0.0836 0.08269 0.07690 -0.1059 0.9241 0.0594
-8.500 -0.0892 0.07921 0.07345 -0.1070 0.9160 0.0595
-8.250 -0.0942 0.07504 0.06928 -0.1094 0.9088 0.0597
-7.750 -0.1659 0.05003 0.04379 -0.1305 0.8869 0.0622
-7.500 -0.1616 0.04902 0.04275 -0.1287 0.8788 0.0629
-7.250 -0.1513 0.04593 0.03946 -0.1299 0.8731 0.0640
-7.000 -0.1408 0.03968 0.03256 -0.1336 0.8690 0.0665
-6.750 -0.1356 0.03571 0.02793 -0.1332 0.8620 0.0693
-6.500 -0.1160 0.03541 0.02763 -0.1322 0.8565 0.0709
-6.250 -0.0912 0.03370 0.02557 -0.1329 0.8530 0.0746
-6.000 -0.0621 0.03225 0.02385 -0.1340 0.8505 0.0780
-5.750 -0.0304 0.03130 0.02273 -0.1351 0.8485 0.0815
-5.500 -0.0237 0.03045 0.02150 -0.1321 0.8393 0.0853
-5.250 0.0036 0.03020 0.02133 -0.1322 0.8355 0.0881
-5.000 0.0348 0.02938 0.02025 -0.1330 0.8328 0.0933
-4.750 0.0687 0.02869 0.01948 -0.1342 0.8305 0.0976
-4.500 0.0813 0.02869 0.01945 -0.1317 0.8211 0.1009
-4.250 0.1122 0.02795 0.01844 -0.1321 0.8165 0.1067
-4.000 0.1479 0.02739 0.01793 -0.1333 0.8131 0.1116
-3.750 0.1677 0.02706 0.01742 -0.1318 0.8044 0.1162
-3.500 0.1972 0.02634 0.01661 -0.1319 0.7987 0.1199
-3.250 0.2321 0.02559 0.01581 -0.1329 0.7952 0.1234
-3.000 0.2540 0.02528 0.01543 -0.1318 0.7881 0.1265
-2.750 0.2794 0.02490 0.01492 -0.1312 0.7821 0.1298
-2.500 0.3120 0.02424 0.01418 -0.1317 0.7784 0.1327
-2.250 0.3468 0.02354 0.01349 -0.1327 0.7756 0.1358
-2.000 0.3611 0.02361 0.01359 -0.1304 0.7657 0.1386
-1.750 0.3927 0.02311 0.01303 -0.1307 0.7612 0.1430
-1.500 0.4278 0.02250 0.01234 -0.1316 0.7580 0.1472
-1.250 0.4434 0.02250 0.01243 -0.1295 0.7480 0.1503
-1.000 0.4747 0.02202 0.01197 -0.1298 0.7431 0.1557
-0.750 0.5030 0.02171 0.01162 -0.1296 0.7370 0.1626
-0.500 0.5253 0.02152 0.01153 -0.1285 0.7284 0.1697
-0.250 0.5592 0.02101 0.01101 -0.1291 0.7235 0.1810
0.000 0.5786 0.02098 0.01109 -0.1276 0.7136 0.1923
0.250 0.6098 0.02055 0.01073 -0.1279 0.7071 0.2142
0.500 0.6325 0.02043 0.01075 -0.1268 0.6975 0.2455
0.750 0.6629 0.02004 0.01049 -0.1270 0.6896 0.2983
1.000 0.6867 0.01986 0.01051 -0.1262 0.6794 0.3608
1.250 0.7164 0.01920 0.01030 -0.1263 0.6710 0.5013
1.750 0.7711 0.01816 0.01007 -0.1247 0.6497 1.0000
2.000 0.7950 0.01827 0.01005 -0.1238 0.6371 1.0000
2.250 0.8194 0.01838 0.01004 -0.1230 0.6244 1.0000
2.500 0.8469 0.01841 0.00992 -0.1227 0.6123 1.0000
2.750 0.8730 0.01850 0.00986 -0.1221 0.5991 1.0000
3.000 0.8958 0.01870 0.00996 -0.1211 0.5849 1.0000
3.250 0.9200 0.01889 0.01004 -0.1203 0.5714 1.0000
3.500 0.9452 0.01908 0.01008 -0.1197 0.5586 1.0000
3.750 0.9695 0.01931 0.01019 -0.1190 0.5457 1.0000
4.000 0.9917 0.01962 0.01041 -0.1180 0.5330 1.0000
4.250 1.0157 0.01991 0.01059 -0.1173 0.5220 1.0000
4.500 1.0394 0.02023 0.01079 -0.1165 0.5114 1.0000
4.750 1.0618 0.02060 0.01109 -0.1156 0.5014 1.0000
5.000 1.0861 0.02094 0.01131 -0.1150 0.4925 1.0000
5.250 1.1075 0.02135 0.01169 -0.1140 0.4837 1.0000
5.500 1.1313 0.02173 0.01198 -0.1134 0.4759 1.0000
5.750 1.1535 0.02216 0.01237 -0.1125 0.4684 1.0000
6.000 1.1750 0.02260 0.01278 -0.1116 0.4610 1.0000
6.250 1.2014 0.02300 0.01306 -0.1114 0.4547 1.0000
6.500 1.2200 0.02351 0.01364 -0.1101 0.4477 1.0000
6.750 1.2424 0.02398 0.01407 -0.1093 0.4412 1.0000
7.000 1.2676 0.02444 0.01446 -0.1090 0.4353 1.0000
7.250 1.2852 0.02501 0.01510 -0.1076 0.4288 1.0000
7.500 1.3066 0.02552 0.01560 -0.1067 0.4226 1.0000
7.750 1.3314 0.02601 0.01603 -0.1064 0.4169 1.0000
8.000 1.3463 0.02665 0.01678 -0.1046 0.4105 1.0000
8.250 1.3658 0.02722 0.01737 -0.1035 0.4044 1.0000
8.500 1.3912 0.02770 0.01779 -0.1033 0.3991 1.0000
8.750 1.4027 0.02846 0.01869 -0.1012 0.3930 1.0000
9.000 1.4194 0.02911 0.01940 -0.0997 0.3871 1.0000
9.250 1.4426 0.02960 0.01984 -0.0992 0.3814 1.0000
9.500 1.4503 0.03049 0.02089 -0.0967 0.3749 1.0000
9.750 1.4625 0.03124 0.02171 -0.0947 0.3682 1.0000
10.000 1.4806 0.03182 0.02226 -0.0936 0.3620 1.0000
10.250 1.4845 0.03291 0.02353 -0.0908 0.3549 1.0000
10.500 1.4954 0.03372 0.02438 -0.0889 0.3481 1.0000
10.750 1.5052 0.03465 0.02538 -0.0869 0.3415 1.0000
11.000 1.5106 0.03582 0.02669 -0.0846 0.3344 1.0000
11.250 1.5228 0.03663 0.02750 -0.0830 0.3283 1.0000
11.500 1.5260 0.03805 0.02909 -0.0807 0.3214 1.0000
11.750 1.5318 0.03930 0.03043 -0.0787 0.3146 1.0000
12.000 1.5377 0.04058 0.03178 -0.0768 0.3077 1.0000
12.250 1.5381 0.04229 0.03363 -0.0746 0.2996 1.0000
12.500 1.5420 0.04375 0.03512 -0.0727 0.2921 1.0000
12.750 1.5407 0.04578 0.03730 -0.0708 0.2837 1.0000
13.000 1.5425 0.04754 0.03910 -0.0690 0.2761 1.0000
13.250 1.5397 0.04989 0.04160 -0.0674 0.2676 1.0000
13.500 1.5399 0.05203 0.04380 -0.0659 0.2599 1.0000
13.750 1.5365 0.05469 0.04658 -0.0645 0.2516 1.0000
14.000 1.5342 0.05730 0.04926 -0.0633 0.2439 1.0000
14.250 1.5291 0.06037 0.05245 -0.0623 0.2355 1.0000
14.500 1.5232 0.06366 0.05582 -0.0615 0.2271 1.0000
14.750 1.5159 0.06718 0.05940 -0.0608 0.2184 1.0000
15.000 1.5060 0.07125 0.06361 -0.0604 0.2096 1.0000
15.250 1.4970 0.07527 0.06766 -0.0602 0.2012 1.0000
15.500 1.4849 0.07994 0.07246 -0.0603 0.1930 1.0000
15.750 1.4738 0.08450 0.07710 -0.0605 0.1853 1.0000
16.000 1.4604 0.08958 0.08227 -0.0610 0.1772 1.0000
16.250 1.4472 0.09475 0.08752 -0.0618 0.1693 1.0000
16.500 1.4344 0.09991 0.09272 -0.0627 0.1608 1.0000
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