GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 365 AIRFOIL (goe365-il) Reynolds number: 200,000 Max Cl/Cd: 79.12 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe365-il-200000.txt Download as CSV file: xf-goe365-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 365 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2694 0.11138 0.10799 -0.0388 1.0000 0.0341
-9.750 -0.2751 0.10976 0.10645 -0.0368 1.0000 0.0344
-9.500 -0.2929 0.10957 0.10637 -0.0323 1.0000 0.0346
-9.250 -0.2750 0.10550 0.10230 -0.0368 0.9966 0.0355
-9.000 -0.2563 0.10116 0.09795 -0.0422 0.9922 0.0370
-8.750 -0.2389 0.09670 0.09349 -0.0494 0.9864 0.0386
-8.500 -0.2281 0.09177 0.08857 -0.0639 0.9750 0.0396
-8.250 -0.2096 0.08620 0.08300 -0.0672 0.9719 0.0403
-8.000 -0.1900 0.08298 0.07978 -0.0672 0.9655 0.0412
-7.750 -0.1686 0.07912 0.07590 -0.0718 0.9605 0.0427
-7.500 -0.1536 0.07508 0.07184 -0.0775 0.9510 0.0442
-7.250 -0.1254 0.06850 0.06513 -0.0935 0.9431 0.0474
-7.000 -0.1080 0.06201 0.05836 -0.1038 0.9324 0.0485
-6.750 -0.0836 0.05833 0.05477 -0.1049 0.9302 0.0496
-6.500 -0.0672 0.05592 0.05235 -0.1053 0.9217 0.0511
-6.250 -0.0414 0.05251 0.04882 -0.1093 0.9163 0.0545
-6.000 -0.0282 0.04866 0.04437 -0.1128 0.9044 0.0592
-5.750 -0.0047 0.04504 0.04086 -0.1142 0.9002 0.0607
-5.500 0.0105 0.04310 0.03890 -0.1136 0.8919 0.0626
-5.250 0.0329 0.04084 0.03646 -0.1144 0.8856 0.0666
-5.000 0.0498 0.02200 0.01756 -0.1080 0.8607 0.0733
-4.750 0.0678 0.03611 0.03130 -0.1136 0.8706 0.0753
-4.250 0.1059 0.03255 0.02729 -0.1120 0.8563 0.0886
-4.000 0.1316 0.03092 0.02556 -0.1123 0.8515 0.0946
-3.750 0.1466 0.02950 0.02390 -0.1104 0.8433 0.1043
-3.500 0.1702 0.02856 0.02267 -0.1098 0.8379 0.1186
-3.250 0.1909 0.02682 0.02103 -0.1092 0.8319 0.1254
-3.000 0.2114 0.02577 0.01988 -0.1083 0.8254 0.1430
-2.000 0.3267 0.01998 0.01250 -0.1042 0.8037 0.0831
-1.750 0.3498 0.01872 0.01111 -0.1029 0.7964 0.0774
-1.500 0.3804 0.01854 0.01061 -0.1023 0.7909 0.0712
-1.250 0.4063 0.01746 0.00949 -0.1016 0.7846 0.0696
-1.000 0.4325 0.01676 0.00874 -0.1009 0.7778 0.0689
-0.750 0.4625 0.01616 0.00806 -0.1009 0.7726 0.0690
-0.500 0.4847 0.01591 0.00781 -0.0996 0.7641 0.0704
-0.250 0.5133 0.01544 0.00730 -0.0993 0.7582 0.0713
0.000 0.5346 0.01502 0.00692 -0.0979 0.7495 0.0723
0.250 0.5618 0.01456 0.00642 -0.0974 0.7421 0.0745
0.500 0.5834 0.01433 0.00619 -0.0958 0.7312 0.0773
0.750 0.6088 0.01409 0.00586 -0.0949 0.7203 0.0827
1.000 0.6356 0.01379 0.00549 -0.0941 0.7096 0.0956
1.250 0.7340 0.01146 0.00535 -0.1087 0.6965 1.0000
1.500 0.7554 0.01153 0.00532 -0.1073 0.6868 1.0000
1.750 0.7795 0.01156 0.00522 -0.1063 0.6778 1.0000
2.000 0.7991 0.01162 0.00524 -0.1045 0.6662 1.0000
2.250 0.8205 0.01166 0.00522 -0.1030 0.6551 1.0000
2.500 0.8426 0.01169 0.00516 -0.1016 0.6436 1.0000
2.750 0.8639 0.01172 0.00512 -0.1001 0.6309 1.0000
3.000 0.8841 0.01177 0.00513 -0.0984 0.6166 1.0000
3.250 0.9047 0.01184 0.00513 -0.0968 0.6016 1.0000
3.500 0.9252 0.01193 0.00515 -0.0952 0.5862 1.0000
3.750 0.9455 0.01206 0.00519 -0.0936 0.5700 1.0000
4.000 0.9652 0.01223 0.00527 -0.0918 0.5530 1.0000
4.250 0.9843 0.01244 0.00539 -0.0900 0.5348 1.0000
4.500 1.0030 0.01269 0.00553 -0.0882 0.5161 1.0000
4.750 1.0211 0.01298 0.00572 -0.0862 0.4971 1.0000
5.000 1.0388 0.01331 0.00592 -0.0843 0.4783 1.0000
5.250 1.0559 0.01365 0.00617 -0.0822 0.4592 1.0000
5.500 1.0727 0.01400 0.00645 -0.0801 0.4403 1.0000
5.750 1.0887 0.01438 0.00675 -0.0780 0.4213 1.0000
6.000 1.1038 0.01479 0.00706 -0.0756 0.4023 1.0000
6.250 1.1180 0.01524 0.00741 -0.0732 0.3831 1.0000
6.500 1.1320 0.01567 0.00779 -0.0707 0.3637 1.0000
6.750 1.1450 0.01616 0.00820 -0.0682 0.3453 1.0000
7.000 1.1572 0.01666 0.00862 -0.0655 0.3291 1.0000
7.250 1.1689 0.01718 0.00907 -0.0627 0.3151 1.0000
7.500 1.1813 0.01774 0.00955 -0.0602 0.3035 1.0000
7.750 1.1942 0.01832 0.01007 -0.0578 0.2933 1.0000
8.000 1.2090 0.01885 0.01060 -0.0558 0.2835 1.0000
8.250 1.2236 0.01947 0.01115 -0.0538 0.2760 1.0000
8.500 1.2400 0.01999 0.01172 -0.0522 0.2687 1.0000
8.750 1.2565 0.02065 0.01231 -0.0507 0.2629 1.0000
9.000 1.2733 0.02118 0.01292 -0.0492 0.2570 1.0000
9.250 1.2898 0.02177 0.01353 -0.0477 0.2515 1.0000
9.500 1.3090 0.02246 0.01416 -0.0467 0.2469 1.0000
9.750 1.3246 0.02301 0.01485 -0.0452 0.2419 1.0000
10.000 1.3389 0.02363 0.01550 -0.0435 0.2363 1.0000
10.250 1.3536 0.02434 0.01621 -0.0420 0.2303 1.0000
10.500 1.3643 0.02498 0.01696 -0.0400 0.2241 1.0000
10.750 1.3787 0.02577 0.01767 -0.0386 0.2179 1.0000
11.000 1.3885 0.02648 0.01857 -0.0366 0.2128 1.0000
11.250 1.3988 0.02727 0.01943 -0.0348 0.2072 1.0000
11.500 1.4100 0.02816 0.02033 -0.0333 0.2015 1.0000
11.750 1.4186 0.02904 0.02137 -0.0315 0.1959 1.0000
12.000 1.4280 0.03002 0.02238 -0.0299 0.1907 1.0000
12.250 1.4364 0.03107 0.02355 -0.0283 0.1852 1.0000
12.500 1.4428 0.03220 0.02481 -0.0268 0.1790 1.0000
12.750 1.4485 0.03350 0.02613 -0.0253 0.1730 1.0000
13.000 1.4546 0.03478 0.02760 -0.0240 0.1664 1.0000
13.250 1.4579 0.03635 0.02917 -0.0226 0.1602 1.0000
13.500 1.4639 0.03781 0.03086 -0.0217 0.1518 1.0000
13.750 1.4673 0.03955 0.03268 -0.0207 0.1425 1.0000
14.000 1.4700 0.04147 0.03469 -0.0199 0.1270 1.0000
14.250 1.4673 0.04401 0.03716 -0.0190 0.1061 1.0000
14.500 1.4550 0.04761 0.04061 -0.0181 0.0890 1.0000
14.750 1.4441 0.05126 0.04423 -0.0173 0.0777 1.0000
15.000 1.4360 0.05483 0.04784 -0.0169 0.0605 1.0000
15.250 1.4176 0.05973 0.05263 -0.0168 0.0438 1.0000
15.500 1.4038 0.06437 0.05729 -0.0171 0.0396 1.0000
15.750 1.3898 0.06929 0.06230 -0.0178 0.0372 1.0000
16.000 1.3742 0.07464 0.06777 -0.0188 0.0355 1.0000
16.250 1.3593 0.08017 0.07343 -0.0202 0.0345 1.0000
16.500 1.3447 0.08582 0.07923 -0.0218 0.0335 1.0000
16.750 1.3323 0.09128 0.08486 -0.0235 0.0331 1.0000
17.000 1.3169 0.09736 0.09111 -0.0256 0.0324 1.0000
17.250 1.3033 0.10327 0.09716 -0.0278 0.0321 1.0000
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