GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| 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: 106.32 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe199-il-1000000-n5.txt Download as CSV file: xf-goe199-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3473 0.09595 0.09430 -0.0188 0.9260 0.0061
-8.250 -0.3466 0.09223 0.09050 -0.0201 0.9007 0.0063
-8.000 -0.3482 0.08750 0.08569 -0.0227 0.8795 0.0066
-7.750 -0.3380 0.08393 0.08206 -0.0262 0.8639 0.0068
-7.500 -0.3243 0.08100 0.07906 -0.0293 0.8504 0.0069
-7.250 -0.3090 0.07792 0.07593 -0.0328 0.8390 0.0071
-7.000 -0.2921 0.07485 0.07280 -0.0363 0.8288 0.0073
-6.750 -0.2736 0.07141 0.06931 -0.0403 0.8195 0.0078
-6.500 -0.2533 0.06585 0.06366 -0.0465 0.8101 0.0085
-6.250 -0.2300 0.06088 0.05860 -0.0521 0.8015 0.0090
-6.000 -0.2062 0.05821 0.05586 -0.0552 0.7941 0.0092
-5.750 -0.1812 0.05537 0.05295 -0.0585 0.7879 0.0095
-5.500 -0.1547 0.05212 0.04961 -0.0620 0.7816 0.0101
-5.250 -0.1220 0.04562 0.04294 -0.0682 0.7763 0.0115
-5.000 -0.0949 0.04351 0.04075 -0.0702 0.7699 0.0117
-4.500 -0.0383 0.03879 0.03582 -0.0743 0.7589 0.0126
-4.250 -0.0021 0.03282 0.02956 -0.0780 0.7534 0.0144
-4.000 0.0253 0.03146 0.02810 -0.0790 0.7473 0.0146
-3.750 0.0536 0.02986 0.02640 -0.0800 0.7385 0.0149
-3.500 0.0826 0.02804 0.02439 -0.0809 0.7230 0.0155
-3.250 0.1191 0.02239 0.01823 -0.0822 0.7068 0.0175
-3.000 0.1469 0.02106 0.01666 -0.0827 0.6806 0.0178
-2.750 0.1747 0.02036 0.01579 -0.0831 0.6553 0.0180
-2.500 0.2027 0.01967 0.01494 -0.0835 0.6315 0.0184
-2.250 0.2317 0.01849 0.01352 -0.0838 0.6075 0.0190
-2.000 0.2612 0.01702 0.01174 -0.0841 0.5790 0.0195
-1.750 0.2907 0.01558 0.00994 -0.0843 0.5504 0.0199
-1.500 0.3203 0.01405 0.00805 -0.0844 0.5277 0.0206
-1.250 0.3494 0.01318 0.00687 -0.0845 0.5097 0.0210
-1.000 0.3780 0.01233 0.00580 -0.0847 0.4951 0.0215
-0.750 0.4064 0.01188 0.00523 -0.0849 0.4811 0.0217
-0.500 0.4348 0.01161 0.00487 -0.0851 0.4663 0.0220
-0.250 0.4631 0.01136 0.00451 -0.0852 0.4502 0.0222
0.000 0.4914 0.01115 0.00420 -0.0854 0.4313 0.0225
0.250 0.5194 0.01098 0.00391 -0.0855 0.4090 0.0227
0.500 0.5474 0.01087 0.00366 -0.0856 0.3826 0.0229
0.750 0.5752 0.01085 0.00351 -0.0857 0.3563 0.0233
1.000 0.6030 0.01080 0.00334 -0.0858 0.3326 0.0235
1.250 0.6308 0.01074 0.00318 -0.0859 0.3118 0.0236
1.500 0.6586 0.01072 0.00307 -0.0860 0.2927 0.0238
1.750 0.6865 0.01073 0.00299 -0.0861 0.2758 0.0242
2.000 0.7144 0.01076 0.00295 -0.0862 0.2620 0.0247
2.250 0.7423 0.01081 0.00295 -0.0863 0.2502 0.0252
2.500 0.7700 0.01089 0.00298 -0.0864 0.2376 0.0256
2.750 0.7977 0.01100 0.00303 -0.0865 0.2261 0.0259
3.000 0.8256 0.01101 0.00301 -0.0867 0.2180 0.0264
3.250 0.8534 0.01107 0.00304 -0.0868 0.2120 0.0272
3.500 0.8813 0.01113 0.00311 -0.0869 0.2073 0.0282
3.750 0.9090 0.01122 0.00319 -0.0870 0.2024 0.0288
4.000 0.9366 0.01132 0.00328 -0.0871 0.1979 0.0294
4.250 0.9644 0.01141 0.00338 -0.0872 0.1950 0.0305
4.500 0.9920 0.01151 0.00348 -0.0872 0.1918 0.0316
4.750 1.0194 0.01163 0.00361 -0.0873 0.1885 0.0338
5.000 1.0467 0.01178 0.00377 -0.0874 0.1841 0.0389
5.250 1.0713 0.01038 0.00410 -0.0873 0.1806 1.0000
5.500 1.0985 0.01055 0.00426 -0.0873 0.1762 1.0000
5.750 1.1255 0.01074 0.00444 -0.0874 0.1727 1.0000
6.000 1.1524 0.01095 0.00463 -0.0874 0.1691 1.0000
6.250 1.1794 0.01112 0.00481 -0.0874 0.1655 1.0000
6.500 1.2059 0.01135 0.00501 -0.0874 0.1592 1.0000
6.750 1.2322 0.01159 0.00524 -0.0873 0.1530 1.0000
7.000 1.2583 0.01185 0.00547 -0.0872 0.1441 1.0000
7.250 1.2818 0.01244 0.00586 -0.0868 0.1115 1.0000
7.500 1.3021 0.01346 0.00666 -0.0860 0.0695 1.0000
7.750 1.3229 0.01437 0.00737 -0.0852 0.0359 1.0000
8.000 1.3468 0.01483 0.00782 -0.0848 0.0286 1.0000
8.250 1.3706 0.01527 0.00826 -0.0843 0.0238 1.0000
8.500 1.3942 0.01571 0.00871 -0.0839 0.0196 1.0000
8.750 1.4172 0.01620 0.00918 -0.0834 0.0159 1.0000
9.000 1.4403 0.01664 0.00964 -0.0829 0.0138 1.0000
9.250 1.4625 0.01715 0.01016 -0.0822 0.0118 1.0000
9.500 1.4849 0.01762 0.01067 -0.0816 0.0105 1.0000
9.750 1.5066 0.01811 0.01119 -0.0809 0.0096 1.0000
10.000 1.5274 0.01867 0.01178 -0.0801 0.0086 1.0000
10.250 1.5474 0.01927 0.01242 -0.0791 0.0079 1.0000
10.500 1.5674 0.01981 0.01302 -0.0781 0.0075 1.0000
10.750 1.5864 0.02039 0.01366 -0.0770 0.0070 1.0000
11.000 1.6041 0.02102 0.01433 -0.0757 0.0065 1.0000
11.250 1.6200 0.02173 0.01508 -0.0742 0.0060 1.0000
11.500 1.6335 0.02255 0.01596 -0.0722 0.0056 1.0000
11.750 1.6473 0.02326 0.01675 -0.0704 0.0054 1.0000
12.000 1.6563 0.02406 0.01763 -0.0677 0.0052 1.0000
12.250 1.6646 0.02497 0.01862 -0.0651 0.0050 1.0000
12.500 1.6726 0.02599 0.01972 -0.0627 0.0048 1.0000
12.750 1.6804 0.02713 0.02093 -0.0605 0.0046 1.0000
13.000 1.6872 0.02841 0.02230 -0.0585 0.0045 1.0000
13.250 1.6932 0.02985 0.02382 -0.0566 0.0043 1.0000
13.500 1.6976 0.03150 0.02556 -0.0548 0.0042 1.0000
13.750 1.6998 0.03346 0.02761 -0.0531 0.0040 1.0000
14.000 1.6990 0.03583 0.03009 -0.0516 0.0039 1.0000
14.250 1.6987 0.03827 0.03265 -0.0504 0.0038 1.0000
14.500 1.6991 0.04077 0.03525 -0.0494 0.0037 1.0000
14.750 1.6979 0.04354 0.03814 -0.0487 0.0037 1.0000
15.000 1.6948 0.04665 0.04137 -0.0482 0.0036 1.0000
15.250 1.6901 0.05010 0.04494 -0.0480 0.0036 1.0000
15.500 1.6835 0.05395 0.04891 -0.0481 0.0035 1.0000
15.750 1.6751 0.05819 0.05328 -0.0485 0.0034 1.0000
16.000 1.6646 0.06301 0.05823 -0.0493 0.0034 1.0000
16.250 1.6526 0.06833 0.06368 -0.0506 0.0033 1.0000
16.500 1.6385 0.07409 0.06958 -0.0522 0.0033 1.0000
16.750 1.6224 0.08034 0.07596 -0.0541 0.0033 1.0000
17.000 1.6041 0.08709 0.08285 -0.0562 0.0033 1.0000
17.250 1.5843 0.09414 0.09004 -0.0586 0.0032 1.0000
17.500 1.5643 0.10138 0.09741 -0.0611 0.0032 1.0000
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