GOE 777 AIRFOIL (goe777-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 777 AIRFOIL (goe777-il) Reynolds number: 200,000 Max Cl/Cd: 54.58 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe777-il-200000.txt Download as CSV file: xf-goe777-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 777 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5098 0.07043 0.06524 -0.0811 0.6800 0.0614
-13.250 -0.5457 0.06318 0.05777 -0.0859 0.6766 0.0611
-13.000 -0.5817 0.05720 0.05149 -0.0888 0.6730 0.0609
-12.750 -0.6139 0.05249 0.04644 -0.0893 0.6692 0.0609
-12.500 -0.6416 0.04867 0.04230 -0.0876 0.6648 0.0611
-12.250 -0.6651 0.04560 0.03882 -0.0843 0.6604 0.0614
-12.000 -0.6631 0.04323 0.03623 -0.0828 0.6553 0.0620
-11.750 -0.6398 0.04245 0.03548 -0.0825 0.6501 0.0628
-11.500 -0.6245 0.04131 0.03424 -0.0816 0.6459 0.0635
-11.250 -0.6135 0.03972 0.03249 -0.0804 0.6419 0.0644
-11.000 -0.6041 0.03797 0.03048 -0.0789 0.6381 0.0656
-10.750 -0.5972 0.03603 0.02812 -0.0769 0.6347 0.0670
-10.500 -0.5838 0.03435 0.02614 -0.0755 0.6315 0.0683
-10.250 -0.5594 0.03357 0.02537 -0.0752 0.6282 0.0694
-10.000 -0.5373 0.03275 0.02446 -0.0747 0.6252 0.0708
-9.750 -0.5172 0.03163 0.02317 -0.0738 0.6225 0.0724
-9.500 -0.4998 0.03057 0.02174 -0.0724 0.6197 0.0743
-9.250 -0.4744 0.02954 0.02078 -0.0723 0.6166 0.0760
-9.000 -0.4495 0.02892 0.02014 -0.0719 0.6135 0.0780
-8.750 -0.4265 0.02816 0.01918 -0.0712 0.6107 0.0805
-8.500 -0.4026 0.02722 0.01807 -0.0706 0.6082 0.0827
-8.250 -0.3766 0.02664 0.01749 -0.0704 0.6060 0.0851
-8.000 -0.3518 0.02620 0.01695 -0.0699 0.6038 0.0884
-7.750 -0.3262 0.02542 0.01615 -0.0696 0.6018 0.0916
-7.500 -0.3003 0.02491 0.01570 -0.0694 0.5997 0.0950
-7.250 -0.2752 0.02457 0.01519 -0.0688 0.5975 0.0988
-7.000 -0.2485 0.02379 0.01458 -0.0688 0.5951 0.1027
-6.750 -0.2229 0.02345 0.01416 -0.0684 0.5926 0.1072
-6.500 -0.1969 0.02284 0.01359 -0.0681 0.5902 0.1114
-6.250 -0.1709 0.02251 0.01326 -0.0677 0.5883 0.1160
-6.000 -0.1450 0.02216 0.01286 -0.0674 0.5864 0.1206
-5.750 -0.1197 0.02185 0.01260 -0.0670 0.5846 0.1254
-5.500 -0.0941 0.02178 0.01248 -0.0666 0.5824 0.1303
-5.250 -0.0702 0.02131 0.01214 -0.0660 0.5797 0.1354
-5.000 -0.0453 0.02105 0.01193 -0.0655 0.5762 0.1412
-4.750 -0.0212 0.02068 0.01161 -0.0648 0.5726 0.1474
-4.500 0.0037 0.02038 0.01130 -0.0642 0.5690 0.1550
-4.250 0.0283 0.02003 0.01098 -0.0635 0.5660 0.1637
-4.000 0.0531 0.01983 0.01078 -0.0630 0.5635 0.1761
-3.750 0.0758 0.01962 0.01075 -0.0622 0.5612 0.2015
-3.500 0.0939 0.01893 0.01067 -0.0609 0.5587 0.3048
-3.250 0.1131 0.01847 0.01067 -0.0595 0.5558 0.4065
-3.000 0.1334 0.01818 0.01079 -0.0581 0.5529 0.4889
-2.750 0.1568 0.01816 0.01099 -0.0570 0.5501 0.5580
-2.500 0.1823 0.01825 0.01111 -0.0563 0.5475 0.6006
-2.250 0.2087 0.01832 0.01119 -0.0556 0.5450 0.6310
-2.000 0.2359 0.01848 0.01131 -0.0552 0.5425 0.6562
-1.750 0.2608 0.01874 0.01161 -0.0544 0.5396 0.6801
-1.500 0.2845 0.01887 0.01185 -0.0534 0.5361 0.7040
-1.250 0.3094 0.01898 0.01202 -0.0526 0.5326 0.7252
-1.000 0.3353 0.01905 0.01212 -0.0520 0.5293 0.7439
-0.750 0.3619 0.01910 0.01215 -0.0514 0.5263 0.7621
-0.500 0.3893 0.01916 0.01216 -0.0509 0.5237 0.7797
-0.250 0.4172 0.01937 0.01233 -0.0505 0.5210 0.7956
0.000 0.4397 0.01956 0.01263 -0.0495 0.5173 0.8116
0.250 0.4631 0.01969 0.01280 -0.0486 0.5130 0.8286
0.500 0.4885 0.01971 0.01286 -0.0477 0.5091 0.8453
0.750 0.5158 0.01967 0.01279 -0.0472 0.5057 0.8621
1.000 0.5453 0.01963 0.01268 -0.0470 0.5028 0.8787
1.250 0.5737 0.01984 0.01283 -0.0469 0.4995 0.8948
1.500 0.5978 0.02001 0.01312 -0.0463 0.4945 0.9119
1.750 0.6328 0.02012 0.01324 -0.0476 0.4898 0.9259
2.000 0.6740 0.02012 0.01316 -0.0499 0.4861 0.9385
2.250 0.7190 0.02013 0.01302 -0.0529 0.4829 0.9509
2.500 0.7616 0.02041 0.01330 -0.0560 0.4781 0.9622
2.750 0.8069 0.02056 0.01348 -0.0599 0.4719 0.9696
3.000 0.8514 0.02046 0.01329 -0.0634 0.4676 0.9789
3.250 0.9025 0.02026 0.01293 -0.0680 0.4640 0.9842
3.500 0.9457 0.02047 0.01318 -0.0718 0.4581 0.9930
3.750 0.9925 0.02048 0.01319 -0.0761 0.4522 0.9998
4.000 1.0050 0.02034 0.01296 -0.0740 0.4489 1.0000
4.250 1.0229 0.02022 0.01271 -0.0725 0.4460 1.0000
4.500 1.0304 0.02050 0.01304 -0.0695 0.4413 1.0000
4.750 1.0414 0.02071 0.01328 -0.0669 0.4364 1.0000
5.000 1.0608 0.02074 0.01324 -0.0656 0.4326 1.0000
5.250 1.0846 0.02070 0.01309 -0.0650 0.4296 1.0000
5.500 1.1025 0.02096 0.01332 -0.0636 0.4259 1.0000
5.750 1.1127 0.02139 0.01383 -0.0609 0.4211 1.0000
6.000 1.1316 0.02157 0.01398 -0.0597 0.4173 1.0000
6.250 1.1552 0.02162 0.01396 -0.0591 0.4142 1.0000
6.500 1.1834 0.02168 0.01388 -0.0593 0.4114 1.0000
6.750 1.1908 0.02232 0.01465 -0.0565 0.4071 1.0000
7.000 1.2057 0.02277 0.01514 -0.0549 0.4034 1.0000
7.250 1.2261 0.02306 0.01541 -0.0540 0.4004 1.0000
7.500 1.2502 0.02326 0.01555 -0.0537 0.3978 1.0000
7.750 1.2799 0.02346 0.01564 -0.0543 0.3954 1.0000
8.000 1.2873 0.02427 0.01657 -0.0518 0.3924 1.0000
8.250 1.2937 0.02505 0.01744 -0.0492 0.3893 1.0000
8.500 1.3058 0.02568 0.01810 -0.0474 0.3866 1.0000
8.750 1.3245 0.02615 0.01856 -0.0466 0.3842 1.0000
9.000 1.3493 0.02645 0.01883 -0.0466 0.3819 1.0000
9.250 1.3824 0.02665 0.01894 -0.0478 0.3798 1.0000
9.500 1.3855 0.02775 0.02014 -0.0452 0.3773 1.0000
9.750 1.3780 0.02935 0.02190 -0.0418 0.3746 1.0000
10.000 1.3780 0.03086 0.02351 -0.0396 0.3720 1.0000
10.250 1.3867 0.03205 0.02476 -0.0385 0.3697 1.0000
10.500 1.4044 0.03282 0.02554 -0.0381 0.3677 1.0000
10.750 1.4314 0.03315 0.02585 -0.0384 0.3660 1.0000
11.000 1.4683 0.03309 0.02573 -0.0396 0.3644 1.0000
11.250 1.4791 0.03440 0.02709 -0.0388 0.3623 1.0000
11.500 0.8174 0.11431 0.10820 -0.0329 0.3154 1.0000
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