GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.17 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe199-il-1000000.txt Download as CSV file: xf-goe199-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 199 (L.F.G. 5406) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3823 0.11321 0.11162 -0.0086 1.0000 0.0113
-9.250 -0.3773 0.10974 0.10816 -0.0108 1.0000 0.0113
-9.000 -0.3719 0.10631 0.10475 -0.0128 1.0000 0.0113
-8.750 -0.3658 0.10249 0.10094 -0.0129 1.0000 0.0115
-8.500 -0.3587 0.09961 0.09807 -0.0139 1.0000 0.0116
-8.250 -0.3518 0.09682 0.09529 -0.0152 1.0000 0.0117
-8.000 -0.3455 0.09404 0.09253 -0.0166 1.0000 0.0119
-7.750 -0.3405 0.09133 0.08984 -0.0179 1.0000 0.0121
-7.250 -0.3089 0.08408 0.08260 -0.0270 0.9763 0.0135
-7.000 -0.2883 0.07943 0.07788 -0.0345 0.9514 0.0141
-6.750 -0.2708 0.07504 0.07340 -0.0405 0.9276 0.0141
-6.500 -0.2516 0.07075 0.06900 -0.0455 0.9090 0.0142
-6.250 -0.2406 0.06679 0.06497 -0.0462 0.8939 0.0143
-6.000 -0.2240 0.06405 0.06216 -0.0477 0.8807 0.0145
-5.750 -0.2035 0.06125 0.05930 -0.0502 0.8695 0.0148
-5.500 -0.1806 0.05833 0.05630 -0.0531 0.8595 0.0152
-5.250 -0.1554 0.05524 0.05311 -0.0564 0.8500 0.0163
-5.000 -0.1096 0.04973 0.04738 -0.0642 0.8418 0.0174
-4.750 -0.0808 0.04597 0.04346 -0.0670 0.8340 0.0175
-4.500 -0.0592 0.04181 0.03920 -0.0691 0.8267 0.0177
-4.250 -0.0359 0.03981 0.03713 -0.0701 0.8193 0.0180
-4.000 -0.0100 0.03786 0.03510 -0.0714 0.8117 0.0185
-3.750 0.0183 0.03566 0.03275 -0.0727 0.8014 0.0196
-3.500 0.0591 0.03241 0.02918 -0.0744 0.7891 0.0212
-3.250 0.0892 0.02969 0.02623 -0.0752 0.7754 0.0213
-3.000 0.1162 0.02570 0.02201 -0.0766 0.7645 0.0217
-2.750 0.1426 0.02440 0.02060 -0.0772 0.7550 0.0221
-2.500 0.1706 0.02305 0.01915 -0.0778 0.7464 0.0226
-2.250 0.1995 0.02165 0.01759 -0.0782 0.7379 0.0235
-2.000 0.2325 0.02047 0.01612 -0.0779 0.7284 0.0258
-1.750 0.2625 0.01921 0.01463 -0.0780 0.7184 0.0259
-1.500 0.2921 0.01785 0.01299 -0.0782 0.7085 0.0260
1.750 0.3095 0.03477 0.03145 -0.0557 0.5247 0.0314
2.000 0.6893 0.00982 0.00292 -0.0801 0.4109 0.0347
2.250 0.7169 0.00986 0.00280 -0.0801 0.3787 0.0335
2.500 0.7444 0.01000 0.00278 -0.0802 0.3473 0.0329
2.750 0.7720 0.01009 0.00276 -0.0803 0.3209 0.0330
3.000 0.7996 0.01020 0.00276 -0.0804 0.2995 0.0341
3.250 0.8272 0.01033 0.00281 -0.0804 0.2793 0.0354
3.500 0.8547 0.01050 0.00289 -0.0805 0.2617 0.0366
3.750 0.8823 0.01065 0.00298 -0.0806 0.2485 0.0378
4.000 0.9099 0.01079 0.00309 -0.0807 0.2383 0.0398
4.250 0.9374 0.01095 0.00321 -0.0807 0.2294 0.0467
4.500 0.9624 0.00942 0.00351 -0.0807 0.2234 1.0000
4.750 0.9897 0.00964 0.00366 -0.0808 0.2156 1.0000
5.000 1.0171 0.00982 0.00382 -0.0808 0.2104 1.0000
5.250 1.0444 0.01000 0.00397 -0.0809 0.2055 1.0000
5.500 1.0714 0.01024 0.00417 -0.0809 0.1995 1.0000
5.750 1.0987 0.01039 0.00433 -0.0809 0.1951 1.0000
6.000 1.1257 0.01059 0.00450 -0.0809 0.1892 1.0000
6.250 1.1524 0.01083 0.00471 -0.0809 0.1838 1.0000
6.500 1.1796 0.01097 0.00488 -0.0810 0.1801 1.0000
6.750 1.2063 0.01118 0.00509 -0.0809 0.1749 1.0000
7.000 1.2327 0.01142 0.00531 -0.0809 0.1686 1.0000
7.250 1.2591 0.01164 0.00552 -0.0809 0.1607 1.0000
7.500 1.2850 0.01193 0.00577 -0.0808 0.1492 1.0000
7.750 1.3024 0.01338 0.00673 -0.0796 0.0715 1.0000
8.000 1.3216 0.01457 0.00767 -0.0786 0.0305 1.0000
8.250 1.3451 0.01510 0.00820 -0.0781 0.0257 1.0000
8.500 1.3685 0.01562 0.00876 -0.0776 0.0223 1.0000
8.750 1.3920 0.01609 0.00926 -0.0771 0.0202 1.0000
9.000 1.4134 0.01682 0.01003 -0.0763 0.0176 1.0000
9.250 1.4368 0.01722 0.01046 -0.0758 0.0166 1.0000
9.500 1.4592 0.01771 0.01099 -0.0752 0.0154 1.0000
9.750 1.4799 0.01838 0.01169 -0.0743 0.0142 1.0000
10.000 1.4978 0.01928 0.01270 -0.0730 0.0132 1.0000
10.250 1.5185 0.01983 0.01330 -0.0721 0.0127 1.0000
10.500 1.5378 0.02046 0.01399 -0.0710 0.0121 1.0000
10.750 1.5562 0.02111 0.01469 -0.0699 0.0114 1.0000
11.000 1.5728 0.02184 0.01546 -0.0684 0.0108 1.0000
11.250 1.5806 0.02314 0.01686 -0.0657 0.0102 1.0000
11.500 1.5880 0.02430 0.01814 -0.0629 0.0098 1.0000
11.750 1.5964 0.02514 0.01906 -0.0601 0.0096 1.0000
12.000 1.6031 0.02616 0.02017 -0.0573 0.0094 1.0000
12.250 1.6090 0.02737 0.02146 -0.0548 0.0091 1.0000
12.500 1.6143 0.02873 0.02292 -0.0525 0.0089 1.0000
12.750 1.6191 0.03025 0.02453 -0.0505 0.0086 1.0000
13.000 1.6232 0.03196 0.02632 -0.0488 0.0084 1.0000
13.250 1.6263 0.03386 0.02831 -0.0472 0.0082 1.0000
13.500 1.6273 0.03610 0.03065 -0.0459 0.0080 1.0000
13.750 1.6249 0.03882 0.03346 -0.0448 0.0078 1.0000
14.000 1.6180 0.04220 0.03696 -0.0438 0.0077 1.0000
14.250 1.6052 0.04647 0.04138 -0.0432 0.0075 1.0000
14.500 1.5879 0.05153 0.04659 -0.0431 0.0074 1.0000
14.750 1.5687 0.05714 0.05235 -0.0435 0.0073 1.0000
15.000 1.5665 0.06077 0.05610 -0.0441 0.0072 1.0000
15.250 1.5620 0.06489 0.06033 -0.0450 0.0071 1.0000
15.500 1.5553 0.06949 0.06504 -0.0462 0.0071 1.0000
15.750 1.5465 0.07446 0.07013 -0.0476 0.0070 1.0000
16.000 1.5368 0.07967 0.07546 -0.0491 0.0069 1.0000
16.250 1.5258 0.08516 0.08106 -0.0508 0.0069 1.0000
16.500 1.5147 0.09073 0.08674 -0.0526 0.0068 1.0000
16.750 1.5030 0.09641 0.09254 -0.0545 0.0067 1.0000
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Polar data table (+)
Polar graphs
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