GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 650 AIRFOIL (goe650-il) Reynolds number: 100,000 Max Cl/Cd: 56.04 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe650-il-100000.txt Download as CSV file: xf-goe650-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 650 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3754 0.10285 0.09799 -0.0236 1.0000 0.1645
-8.000 -0.6126 0.06355 0.05874 -0.0499 1.0000 0.1026
-7.750 -0.6428 0.04994 0.04450 -0.0593 1.0000 0.1020
-7.500 -0.6445 0.04147 0.03514 -0.0638 1.0000 0.1037
-7.250 -0.6279 0.04125 0.03510 -0.0622 1.0000 0.1062
-7.000 -0.6120 0.04025 0.03406 -0.0614 1.0000 0.1096
-6.750 -0.5980 0.03568 0.02854 -0.0632 1.0000 0.1158
-6.500 -0.5803 0.03523 0.02831 -0.0619 1.0000 0.1196
-6.250 -0.5564 0.03357 0.02625 -0.0627 0.9984 0.1274
-6.000 -0.5184 0.03336 0.02611 -0.0653 0.9927 0.1373
-5.750 -0.4839 0.03260 0.02518 -0.0675 0.9864 0.1492
-5.500 -0.4472 0.03203 0.02438 -0.0700 0.9807 0.1620
-5.250 -0.4159 0.03176 0.02388 -0.0712 0.9742 0.1734
-5.000 -0.3784 0.03190 0.02418 -0.0734 0.9693 0.1834
-4.750 -0.3532 0.03134 0.02340 -0.0737 0.9626 0.1934
-4.500 -0.3174 0.03162 0.02365 -0.0755 0.9571 0.2053
-4.250 -0.2906 0.03149 0.02359 -0.0757 0.9507 0.2140
-4.000 -0.2581 0.03103 0.02283 -0.0771 0.9446 0.2231
-3.750 -0.2216 0.03064 0.02243 -0.0791 0.9397 0.2299
-3.500 -0.1979 0.03024 0.02192 -0.0787 0.9320 0.2366
-3.250 -0.1596 0.02982 0.02134 -0.0809 0.9267 0.2449
-3.000 -0.1340 0.02964 0.02114 -0.0808 0.9193 0.2521
-2.750 -0.1010 0.02930 0.02063 -0.0819 0.9129 0.2608
-2.500 -0.0603 0.02926 0.02060 -0.0843 0.9079 0.2716
-2.250 -0.0396 0.02904 0.02034 -0.0833 0.8984 0.2800
-2.000 0.0018 0.02893 0.02011 -0.0857 0.8933 0.2934
-1.750 0.0224 0.02893 0.02026 -0.0846 0.8840 0.3030
-1.500 0.0605 0.02881 0.02016 -0.0864 0.8777 0.3184
-1.250 0.0876 0.02882 0.02017 -0.0863 0.8692 0.3335
-1.000 0.1207 0.02878 0.02019 -0.0871 0.8618 0.3518
-0.750 0.1673 0.02863 0.02014 -0.0900 0.8577 0.3756
-0.500 0.1820 0.02879 0.02035 -0.0879 0.8454 0.3924
-0.250 0.2291 0.02853 0.02012 -0.0906 0.8409 0.4220
0.000 0.2499 0.02849 0.02018 -0.0892 0.8279 0.4421
0.250 0.3061 0.02770 0.01946 -0.0928 0.8233 0.4743
0.500 0.3274 0.02760 0.01943 -0.0913 0.8098 0.4948
0.750 0.3807 0.02670 0.01866 -0.0945 0.8063 0.5242
1.000 0.3979 0.02681 0.01883 -0.0924 0.7931 0.5441
1.250 0.4502 0.02576 0.01792 -0.0953 0.7898 0.5742
1.500 0.4682 0.02579 0.01802 -0.0932 0.7771 0.5962
1.750 0.5242 0.02462 0.01698 -0.0967 0.7736 0.6320
2.000 0.5521 0.02434 0.01683 -0.0961 0.7627 0.6626
2.250 0.6058 0.02310 0.01580 -0.0993 0.7575 0.7124
2.750 0.7253 0.02082 0.01406 -0.1093 0.7407 1.0000
3.000 0.7620 0.02046 0.01357 -0.1101 0.7295 1.0000
3.250 0.8098 0.01970 0.01269 -0.1125 0.7200 1.0000
3.500 0.8370 0.01954 0.01246 -0.1116 0.7050 1.0000
3.750 0.8665 0.01931 0.01217 -0.1111 0.6899 1.0000
4.000 0.8965 0.01903 0.01184 -0.1105 0.6736 1.0000
4.250 0.9250 0.01880 0.01153 -0.1098 0.6559 1.0000
4.500 0.9529 0.01856 0.01122 -0.1089 0.6362 1.0000
4.750 0.9820 0.01834 0.01087 -0.1081 0.6151 1.0000
5.000 1.0016 0.01839 0.01085 -0.1059 0.5896 1.0000
5.250 1.0288 0.01840 0.01064 -0.1050 0.5639 1.0000
5.500 1.0486 0.01871 0.01079 -0.1030 0.5355 1.0000
5.750 1.0711 0.01913 0.01099 -0.1016 0.5086 1.0000
6.000 1.0902 0.01966 0.01136 -0.0997 0.4824 1.0000
6.250 1.1111 0.02021 0.01171 -0.0982 0.4591 1.0000
6.500 1.1275 0.02078 0.01220 -0.0959 0.4367 1.0000
6.750 1.1452 0.02136 0.01268 -0.0940 0.4166 1.0000
7.000 1.1635 0.02196 0.01317 -0.0922 0.3982 1.0000
7.250 1.1821 0.02262 0.01371 -0.0905 0.3812 1.0000
7.500 1.2015 0.02333 0.01432 -0.0889 0.3654 1.0000
7.750 1.2217 0.02410 0.01500 -0.0876 0.3508 1.0000
8.000 1.2433 0.02492 0.01571 -0.0866 0.3371 1.0000
8.250 1.2661 0.02578 0.01644 -0.0858 0.3239 1.0000
8.500 1.2830 0.02661 0.01734 -0.0840 0.3116 1.0000
8.750 1.3047 0.02758 0.01828 -0.0831 0.3006 1.0000
9.000 1.3306 0.02855 0.01912 -0.0829 0.2901 1.0000
9.250 1.3453 0.02948 0.02021 -0.0808 0.2805 1.0000
9.500 1.3714 0.03050 0.02110 -0.0807 0.2710 1.0000
9.750 1.3820 0.03133 0.02210 -0.0780 0.2622 1.0000
10.000 1.4052 0.03229 0.02296 -0.0775 0.2537 1.0000
10.250 1.4143 0.03313 0.02400 -0.0746 0.2460 1.0000
10.500 1.4388 0.03405 0.02477 -0.0743 0.2381 1.0000
10.750 1.4428 0.03493 0.02592 -0.0707 0.2315 1.0000
11.000 1.4636 0.03568 0.02657 -0.0698 0.2244 1.0000
11.250 1.4686 0.03667 0.02775 -0.0665 0.2183 1.0000
11.500 1.4763 0.03753 0.02873 -0.0636 0.2124 1.0000
11.750 1.4992 0.03841 0.02949 -0.0632 0.2059 1.0000
12.000 1.4938 0.03947 0.03084 -0.0586 0.2009 1.0000
12.250 1.5016 0.04018 0.03157 -0.0561 0.1948 1.0000
12.500 1.5108 0.04117 0.03260 -0.0539 0.1890 1.0000
12.750 1.5069 0.04243 0.03410 -0.0502 0.1839 1.0000
13.000 1.5192 0.04312 0.03472 -0.0485 0.1779 1.0000
13.250 1.5167 0.04460 0.03639 -0.0454 0.1727 1.0000
13.500 1.5119 0.04604 0.03802 -0.0424 0.1673 1.0000
13.750 1.5222 0.04687 0.03873 -0.0408 0.1605 1.0000
14.000 1.5067 0.04907 0.04127 -0.0374 0.1554 1.0000
14.250 1.5096 0.05015 0.04226 -0.0355 0.1482 1.0000
14.500 1.4943 0.05285 0.04524 -0.0330 0.1422 1.0000
14.750 1.4924 0.05449 0.04679 -0.0313 0.1343 1.0000
15.000 1.4738 0.05797 0.05055 -0.0295 0.1276 1.0000
15.250 1.4708 0.06019 0.05261 -0.0284 0.1194 1.0000
15.500 1.4515 0.06433 0.05703 -0.0274 0.1132 1.0000
15.750 1.4492 0.06698 0.05956 -0.0268 0.1066 1.0000
16.000 1.4320 0.07153 0.06439 -0.0267 0.1019 1.0000
16.250 1.4405 0.07327 0.06587 -0.0261 0.0961 1.0000
16.500 1.4198 0.07875 0.07172 -0.0267 0.0934 1.0000
16.750 1.4071 0.08347 0.07665 -0.0275 0.0903 1.0000
17.000 1.4154 0.08532 0.07837 -0.0272 0.0864 1.0000
17.250 1.4046 0.09013 0.08336 -0.0281 0.0842 1.0000
17.500 1.3818 0.09682 0.09035 -0.0304 0.0827 1.0000
17.750 1.3585 0.10396 0.09776 -0.0333 0.0815 1.0000
18.000 1.3310 0.11225 0.10631 -0.0372 0.0807 1.0000
18.250 1.2748 0.12662 0.12104 -0.0455 0.0816 1.0000
18.500 1.3509 0.11572 0.10964 -0.0372 0.0754 1.0000
18.750 1.3131 0.12630 0.12052 -0.0432 0.0754 1.0000
19.000 0.9775 0.22871 0.22317 -0.1082 0.1265 1.0000
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