GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 385 AIRFOIL (goe385-il) Reynolds number: 100,000 Max Cl/Cd: 51.81 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe385-il-100000.txt Download as CSV file: xf-goe385-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 385 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2830 0.10851 0.10394 -0.0296 1.0000 0.0666
-9.500 -0.2920 0.10661 0.10212 -0.0326 1.0000 0.0671
-9.250 -0.3000 0.10434 0.09991 -0.0353 1.0000 0.0673
-9.000 -0.2661 0.09599 0.09153 -0.0298 1.0000 0.0707
-8.750 -0.2608 0.09262 0.08818 -0.0298 1.0000 0.0732
-8.500 -0.2593 0.08940 0.08501 -0.0304 1.0000 0.0758
-8.250 -0.2612 0.08636 0.08202 -0.0314 1.0000 0.0783
-7.500 -0.3479 0.08772 0.08325 -0.0286 1.0000 0.0763
-7.250 -0.3493 0.08485 0.08046 -0.0316 1.0000 0.0789
-7.000 -0.3562 0.08275 0.07840 -0.0380 1.0000 0.0812
-6.750 -0.3646 0.08166 0.07715 -0.0421 1.0000 0.0820
-6.500 -0.3626 0.07612 0.07185 -0.0375 1.0000 0.0834
-6.250 -0.3630 0.07365 0.06949 -0.0332 1.0000 0.0853
-6.000 -0.3662 0.07171 0.06761 -0.0307 1.0000 0.0878
-5.750 -0.3696 0.06976 0.06567 -0.0296 1.0000 0.0912
-5.500 -0.3676 0.06892 0.06436 -0.0360 1.0000 0.0974
-5.250 -0.3505 0.06338 0.05918 -0.0344 0.9959 0.1015
-5.000 -0.3061 0.05838 0.05388 -0.0441 0.9872 0.1146
-4.750 -0.2650 0.05432 0.04956 -0.0510 0.9787 0.1293
-4.500 -0.2258 0.05030 0.04541 -0.0562 0.9716 0.1453
-4.250 -0.1929 0.04706 0.04218 -0.0593 0.9622 0.1647
-4.000 -0.1538 0.04390 0.03891 -0.0638 0.9549 0.1954
-3.750 -0.1187 0.04126 0.03615 -0.0673 0.9456 0.2378
-2.750 0.0781 0.02832 0.02082 -0.0843 0.9143 0.1456
-2.500 0.1164 0.02617 0.01816 -0.0849 0.9037 0.1188
-2.250 0.1555 0.02491 0.01639 -0.0858 0.8948 0.1105
-2.000 0.1918 0.02322 0.01448 -0.0866 0.8859 0.1052
-1.750 0.2238 0.02211 0.01310 -0.0864 0.8742 0.1014
-1.500 0.2550 0.02116 0.01198 -0.0859 0.8625 0.0999
-1.250 0.2848 0.02024 0.01102 -0.0854 0.8514 0.1023
-1.000 0.3133 0.01949 0.01024 -0.0846 0.8406 0.1061
-0.750 0.3391 0.01896 0.00970 -0.0836 0.8282 0.1079
-0.500 0.3647 0.01855 0.00926 -0.0826 0.8165 0.1106
-0.250 0.3907 0.01813 0.00879 -0.0816 0.8056 0.1154
0.000 0.4178 0.01780 0.00838 -0.0807 0.7954 0.1255
0.250 0.4435 0.01744 0.00817 -0.0800 0.7830 0.1640
0.500 0.4765 0.01525 0.00800 -0.0799 0.7716 1.0000
0.750 0.5022 0.01540 0.00787 -0.0790 0.7599 1.0000
1.000 0.5282 0.01549 0.00774 -0.0781 0.7489 1.0000
1.250 0.5537 0.01561 0.00770 -0.0773 0.7366 1.0000
1.500 0.5792 0.01575 0.00773 -0.0765 0.7237 1.0000
1.750 0.6048 0.01588 0.00774 -0.0758 0.7109 1.0000
2.000 0.6306 0.01599 0.00774 -0.0751 0.6980 1.0000
2.250 0.6566 0.01611 0.00776 -0.0743 0.6850 1.0000
2.500 0.6826 0.01623 0.00777 -0.0736 0.6717 1.0000
2.750 0.7087 0.01639 0.00783 -0.0729 0.6579 1.0000
3.000 0.7347 0.01658 0.00793 -0.0722 0.6436 1.0000
3.250 0.7605 0.01682 0.00810 -0.0716 0.6285 1.0000
3.500 0.7861 0.01710 0.00830 -0.0710 0.6127 1.0000
3.750 0.8117 0.01740 0.00854 -0.0703 0.5964 1.0000
4.000 0.8372 0.01772 0.00883 -0.0697 0.5801 1.0000
4.250 0.8627 0.01805 0.00912 -0.0692 0.5643 1.0000
4.500 0.8882 0.01838 0.00942 -0.0687 0.5489 1.0000
4.750 0.9137 0.01868 0.00970 -0.0682 0.5338 1.0000
5.000 0.9392 0.01897 0.00999 -0.0676 0.5191 1.0000
5.250 0.9646 0.01926 0.01027 -0.0671 0.5049 1.0000
5.500 0.9901 0.01956 0.01056 -0.0667 0.4916 1.0000
5.750 1.0157 0.01988 0.01088 -0.0662 0.4792 1.0000
6.000 1.0417 0.02019 0.01114 -0.0658 0.4675 1.0000
6.250 1.0664 0.02062 0.01165 -0.0653 0.4551 1.0000
6.500 1.0910 0.02112 0.01223 -0.0649 0.4438 1.0000
6.750 1.1160 0.02160 0.01277 -0.0645 0.4330 1.0000
7.000 1.1420 0.02204 0.01317 -0.0642 0.4231 1.0000
7.250 1.1658 0.02259 0.01386 -0.0636 0.4121 1.0000
7.500 1.1895 0.02315 0.01455 -0.0631 0.4012 1.0000
7.750 1.2136 0.02365 0.01512 -0.0626 0.3899 1.0000
8.000 1.2379 0.02412 0.01560 -0.0620 0.3783 1.0000
8.250 1.2607 0.02452 0.01603 -0.0612 0.3645 1.0000
8.500 1.2815 0.02490 0.01650 -0.0602 0.3491 1.0000
8.750 1.3012 0.02530 0.01703 -0.0590 0.3335 1.0000
9.000 1.3198 0.02570 0.01756 -0.0577 0.3174 1.0000
9.250 1.3366 0.02606 0.01807 -0.0561 0.3002 1.0000
9.500 1.3525 0.02646 0.01861 -0.0545 0.2831 1.0000
9.750 1.3654 0.02681 0.01907 -0.0524 0.2635 1.0000
10.000 1.3749 0.02729 0.01979 -0.0500 0.2394 1.0000
10.250 1.3797 0.02805 0.02062 -0.0471 0.2055 1.0000
10.500 1.3701 0.02995 0.02220 -0.0429 0.1422 1.0000
10.750 1.3491 0.03318 0.02503 -0.0381 0.1045 1.0000
11.000 1.3341 0.03651 0.02820 -0.0349 0.0798 1.0000
11.250 1.3235 0.03974 0.03139 -0.0328 0.0701 1.0000
11.500 1.3110 0.04339 0.03497 -0.0314 0.0653 1.0000
11.750 1.3040 0.04676 0.03849 -0.0304 0.0609 1.0000
12.000 1.2960 0.05035 0.04215 -0.0298 0.0576 1.0000
12.250 1.2869 0.05403 0.04577 -0.0289 0.0547 1.0000
12.500 1.2875 0.05685 0.04874 -0.0280 0.0520 1.0000
12.750 1.2908 0.05935 0.05133 -0.0268 0.0496 1.0000
13.000 1.2975 0.06150 0.05353 -0.0253 0.0475 1.0000
13.250 1.3128 0.06298 0.05492 -0.0228 0.0452 1.0000
13.500 1.3329 0.06492 0.05693 -0.0203 0.0434 1.0000
13.750 1.3342 0.06804 0.06033 -0.0199 0.0424 1.0000
14.000 1.3338 0.07143 0.06397 -0.0196 0.0413 1.0000
14.250 1.3315 0.07512 0.06791 -0.0195 0.0404 1.0000
14.500 1.3274 0.07914 0.07217 -0.0197 0.0398 1.0000
14.750 1.3201 0.08364 0.07693 -0.0202 0.0396 1.0000
15.000 1.3089 0.08868 0.08223 -0.0213 0.0395 1.0000
15.250 1.2942 0.09427 0.08809 -0.0230 0.0396 1.0000
15.500 1.2765 0.10049 0.09457 -0.0254 0.0398 1.0000
15.750 1.2563 0.10745 0.10178 -0.0288 0.0400 1.0000
16.000 1.2342 0.11521 0.10977 -0.0330 0.0404 1.0000
16.250 1.2101 0.12390 0.11869 -0.0383 0.0408 1.0000
16.500 1.1844 0.13365 0.12864 -0.0446 0.0414 1.0000
16.750 1.1570 0.14466 0.13981 -0.0519 0.0421 1.0000
17.000 1.1304 0.15644 0.15170 -0.0597 0.0430 1.0000
17.250 1.1106 0.16720 0.16250 -0.0661 0.0438 1.0000
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