GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 364 AIRFOIL (goe364-il) Reynolds number: 500,000 Max Cl/Cd: 104.02 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe364-il-500000-n5.txt Download as CSV file: xf-goe364-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 364 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2433 0.13997 0.13758 -0.0333 1.0000 0.0121
-12.500 -0.2388 0.13745 0.13509 -0.0336 1.0000 0.0125
-12.250 -0.2346 0.13491 0.13256 -0.0338 1.0000 0.0129
-12.000 -0.2270 0.13172 0.12939 -0.0352 0.9995 0.0133
-11.500 -0.2058 0.12239 0.12005 -0.0415 0.9933 0.0111
-11.250 -0.1927 0.11902 0.11669 -0.0441 0.9891 0.0109
-10.750 -0.1692 0.11141 0.10907 -0.0499 0.9786 0.0110
-10.500 -0.1543 0.10771 0.10536 -0.0534 0.9734 0.0109
-10.250 -0.1397 0.10395 0.10160 -0.0569 0.9654 0.0116
-10.000 -0.1192 0.10046 0.09810 -0.0614 0.9585 0.0119
-9.750 -0.0954 0.09649 0.09411 -0.0672 0.9495 0.0124
-9.500 -0.0704 0.09162 0.08919 -0.0742 0.9363 0.0121
-9.250 -0.0340 0.08626 0.08372 -0.0841 0.9055 0.0126
-9.000 -0.0072 0.08187 0.07909 -0.0912 0.8557 0.0128
-8.750 -0.0013 0.07906 0.07606 -0.0924 0.8170 0.0130
-8.500 0.0018 0.07658 0.07346 -0.0927 0.7933 0.0131
-8.250 0.0043 0.07410 0.07091 -0.0930 0.7757 0.0131
-8.000 0.0027 0.07109 0.06786 -0.0936 0.7621 0.0140
-7.750 0.0088 0.06958 0.06631 -0.0935 0.7504 0.0143
-7.500 0.0095 0.06762 0.06432 -0.0933 0.7389 0.0145
-7.250 0.0135 0.06534 0.06202 -0.0943 0.7296 0.0148
-7.000 0.0197 0.06259 0.05923 -0.0961 0.7204 0.0151
-6.750 0.0277 0.05950 0.05611 -0.0984 0.7122 0.0151
-6.500 0.0378 0.05614 0.05269 -0.1011 0.7044 0.0157
-6.250 0.0485 0.05113 0.04758 -0.1054 0.6978 0.0163
-6.000 0.0655 0.04881 0.04520 -0.1071 0.6905 0.0169
-5.750 0.0837 0.04673 0.04305 -0.1083 0.6840 0.0174
-5.500 0.1029 0.04392 0.04015 -0.1102 0.6773 0.0179
-5.000 0.1431 0.03420 0.02998 -0.1148 0.6653 0.0199
-4.750 0.1653 0.03329 0.02901 -0.1149 0.6579 0.0203
-4.500 0.1875 0.03154 0.02711 -0.1150 0.6513 0.0209
-4.250 0.2101 0.02857 0.02393 -0.1152 0.6445 0.0215
-4.000 0.2292 0.02183 0.01652 -0.1144 0.6392 0.0235
-3.750 0.2534 0.02128 0.01588 -0.1141 0.6327 0.0238
-3.500 0.2771 0.01996 0.01437 -0.1135 0.6257 0.0242
-3.000 0.3250 0.01709 0.01098 -0.1120 0.6122 0.0255
-2.750 0.3494 0.01584 0.00940 -0.1111 0.6048 0.0264
-2.500 0.3746 0.01488 0.00817 -0.1104 0.5972 0.0268
-2.250 0.4001 0.01424 0.00729 -0.1097 0.5883 0.0271
-2.000 0.4260 0.01379 0.00665 -0.1091 0.5788 0.0273
-1.750 0.4508 0.01307 0.00581 -0.1085 0.5683 0.0278
-1.500 0.4761 0.01273 0.00539 -0.1079 0.5554 0.0284
-1.250 0.5016 0.01244 0.00501 -0.1073 0.5425 0.0288
-1.000 0.5270 0.01215 0.00462 -0.1066 0.5301 0.0291
-0.750 0.5521 0.01192 0.00429 -0.1059 0.5167 0.0294
-0.500 0.5770 0.01174 0.00401 -0.1052 0.5033 0.0298
0.000 0.6267 0.01148 0.00358 -0.1038 0.4779 0.0306
0.250 0.6515 0.01140 0.00343 -0.1031 0.4664 0.0310
0.500 0.6760 0.01136 0.00332 -0.1023 0.4557 0.0316
0.750 0.7013 0.01135 0.00326 -0.1017 0.4466 0.0322
1.000 0.7258 0.01128 0.00315 -0.1010 0.4394 0.0327
1.250 0.7511 0.01118 0.00305 -0.1004 0.4336 0.0333
1.500 0.7761 0.01116 0.00302 -0.0997 0.4278 0.0339
1.750 0.8012 0.01117 0.00301 -0.0991 0.4225 0.0347
2.000 0.8267 0.01118 0.00302 -0.0986 0.4168 0.0356
2.250 0.8517 0.01124 0.00305 -0.0980 0.4109 0.0365
2.500 0.8767 0.01132 0.00309 -0.0974 0.4056 0.0376
2.750 0.9023 0.01135 0.00313 -0.0969 0.4006 0.0402
3.000 0.9272 0.01142 0.00320 -0.0963 0.3954 0.0431
3.250 0.9517 0.01152 0.00329 -0.0956 0.3904 0.0509
3.500 0.9666 0.01047 0.00361 -0.0935 0.3862 0.6911
4.000 1.0609 0.01038 0.00400 -0.1022 0.3715 1.0000
4.250 1.0847 0.01054 0.00412 -0.1014 0.3645 1.0000
4.500 1.1076 0.01074 0.00426 -0.1004 0.3573 1.0000
4.750 1.1313 0.01090 0.00441 -0.0997 0.3497 1.0000
5.000 1.1538 0.01111 0.00457 -0.0987 0.3417 1.0000
5.250 1.1765 0.01131 0.00474 -0.0977 0.3316 1.0000
5.500 1.1981 0.01156 0.00493 -0.0966 0.3197 1.0000
5.750 1.2190 0.01183 0.00515 -0.0954 0.3068 1.0000
6.000 1.2392 0.01214 0.00538 -0.0941 0.2940 1.0000
6.250 1.2584 0.01249 0.00565 -0.0926 0.2809 1.0000
6.500 1.2771 0.01285 0.00596 -0.0910 0.2687 1.0000
6.750 1.2947 0.01325 0.00629 -0.0893 0.2558 1.0000
7.000 1.3116 0.01364 0.00662 -0.0875 0.2453 1.0000
7.500 1.3443 0.01436 0.00729 -0.0835 0.2314 1.0000
7.750 1.3616 0.01468 0.00762 -0.0818 0.2270 1.0000
8.000 1.3779 0.01506 0.00800 -0.0799 0.2227 1.0000
8.250 1.3947 0.01543 0.00838 -0.0782 0.2192 1.0000
8.500 1.4127 0.01575 0.00875 -0.0767 0.2158 1.0000
8.750 1.4296 0.01614 0.00915 -0.0751 0.2119 1.0000
9.000 1.4451 0.01659 0.00962 -0.0733 0.2079 1.0000
9.250 1.4601 0.01709 0.01013 -0.0715 0.2043 1.0000
9.500 1.4777 0.01747 0.01057 -0.0702 0.2016 1.0000
9.750 1.4943 0.01791 0.01105 -0.0687 0.1984 1.0000
10.000 1.5092 0.01844 0.01161 -0.0671 0.1943 1.0000
10.250 1.5218 0.01911 0.01229 -0.0652 0.1899 1.0000
10.500 1.5378 0.01962 0.01285 -0.0639 0.1844 1.0000
10.750 1.5500 0.02036 0.01358 -0.0622 0.1771 1.0000
11.000 1.5630 0.02107 0.01433 -0.0606 0.1707 1.0000
11.250 1.5745 0.02192 0.01518 -0.0590 0.1633 1.0000
11.500 1.5857 0.02281 0.01609 -0.0575 0.1562 1.0000
12.000 1.6029 0.02507 0.01836 -0.0543 0.1392 1.0000
12.250 1.6090 0.02648 0.01975 -0.0527 0.1303 1.0000
12.500 1.6140 0.02802 0.02129 -0.0512 0.1226 1.0000
12.750 1.6194 0.02959 0.02289 -0.0499 0.1151 1.0000
13.000 1.6216 0.03150 0.02480 -0.0485 0.1076 1.0000
13.250 1.6231 0.03353 0.02684 -0.0472 0.0999 1.0000
13.500 1.6238 0.03568 0.02901 -0.0460 0.0927 1.0000
13.750 1.6225 0.03811 0.03145 -0.0450 0.0863 1.0000
14.000 1.6241 0.04034 0.03372 -0.0441 0.0809 1.0000
14.250 1.6204 0.04315 0.03655 -0.0433 0.0746 1.0000
14.500 1.6170 0.04601 0.03944 -0.0426 0.0669 1.0000
14.750 1.6125 0.04909 0.04255 -0.0421 0.0603 1.0000
15.000 1.5980 0.05337 0.04680 -0.0416 0.0483 1.0000
15.250 1.5735 0.05906 0.05243 -0.0415 0.0316 1.0000
15.500 1.5538 0.06443 0.05782 -0.0418 0.0217 1.0000
15.750 1.5380 0.06951 0.06297 -0.0422 0.0176 1.0000
16.000 1.5283 0.07396 0.06752 -0.0428 0.0157 1.0000
16.250 1.5201 0.07825 0.07192 -0.0435 0.0146 1.0000
16.500 1.5113 0.08275 0.07652 -0.0443 0.0138 1.0000
16.750 1.5037 0.08713 0.08101 -0.0452 0.0130 1.0000
17.000 1.4971 0.09144 0.08543 -0.0461 0.0125 1.0000
17.250 1.4894 0.09593 0.09003 -0.0472 0.0120 1.0000
17.500 1.4806 0.10066 0.09488 -0.0485 0.0115 1.0000
17.750 1.4715 0.10553 0.09985 -0.0499 0.0112 1.0000
18.000 1.4603 0.11081 0.10525 -0.0516 0.0107 1.0000
18.250 1.4508 0.11586 0.11041 -0.0533 0.0105 1.0000
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