GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 177 AIRFOIL (goe177-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.93 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe177-il-1000000.txt Download as CSV file: xf-goe177-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 177 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3302 0.08752 0.08606 -0.0194 1.0000 0.0082
-7.250 -0.3288 0.08460 0.08318 -0.0202 1.0000 0.0082
-7.000 -0.3244 0.08135 0.07995 -0.0221 0.9995 0.0082
-6.750 -0.3049 0.07364 0.07224 -0.0322 0.9949 0.0086
-6.500 -0.2798 0.06972 0.06831 -0.0383 0.9896 0.0089
-6.250 -0.2517 0.06580 0.06437 -0.0448 0.9834 0.0092
-6.000 -0.2252 0.06171 0.06025 -0.0510 0.9732 0.0098
-5.750 -0.1977 0.05713 0.05561 -0.0574 0.9605 0.0109
-5.500 -0.1643 0.05232 0.05072 -0.0639 0.9448 0.0124
-5.250 -0.1184 0.01802 0.01501 -0.0890 0.9342 0.0085
-5.000 -0.0937 0.01464 0.01105 -0.0892 0.9134 0.0087
-4.750 -0.0692 0.01321 0.00928 -0.0887 0.8771 0.0092
-4.500 -0.0442 0.01204 0.00768 -0.0880 0.8317 0.0094
-4.250 -0.0179 0.01101 0.00625 -0.0876 0.7932 0.0096
-4.000 0.0092 0.01047 0.00544 -0.0873 0.7622 0.0104
-3.750 0.0368 0.00997 0.00473 -0.0871 0.7366 0.0112
-3.500 0.0646 0.00967 0.00424 -0.0869 0.7155 0.0121
-3.250 0.0926 0.00944 0.00386 -0.0868 0.6956 0.0125
-3.000 0.1206 0.00857 0.00273 -0.0868 0.6756 0.0144
-2.750 0.1486 0.00842 0.00249 -0.0867 0.6539 0.0167
-2.500 0.1765 0.00833 0.00226 -0.0866 0.6324 0.0186
-2.250 0.2048 0.00799 0.00179 -0.0865 0.6132 0.0241
-2.000 0.2330 0.00781 0.00155 -0.0865 0.5958 0.0361
-1.750 0.2611 0.00780 0.00158 -0.0865 0.5790 0.0621
-1.500 0.2892 0.00784 0.00156 -0.0864 0.5630 0.0711
-1.250 0.3173 0.00794 0.00158 -0.0864 0.5486 0.0752
-1.000 0.3452 0.00792 0.00148 -0.0864 0.5305 0.0804
-0.750 0.3730 0.00798 0.00145 -0.0864 0.5073 0.0850
-0.500 0.4009 0.00805 0.00140 -0.0863 0.4853 0.0881
-0.250 0.4288 0.00811 0.00136 -0.0863 0.4656 0.0892
0.000 0.4567 0.00812 0.00127 -0.0863 0.4451 0.0930
0.250 0.4846 0.00814 0.00124 -0.0863 0.4280 0.0979
0.500 0.5125 0.00820 0.00122 -0.0863 0.4105 0.1015
0.750 0.5403 0.00827 0.00122 -0.0863 0.3931 0.1089
1.000 0.5681 0.00830 0.00124 -0.0863 0.3759 0.1302
1.250 0.5959 0.00815 0.00133 -0.0865 0.3594 0.2556
1.500 0.6236 0.00810 0.00144 -0.0866 0.3440 0.3565
1.750 0.6422 0.00686 0.00161 -0.0849 0.3321 0.9380
2.000 0.6723 0.00696 0.00163 -0.0853 0.3174 1.0000
2.250 0.6999 0.00712 0.00170 -0.0853 0.3032 1.0000
2.500 0.7273 0.00731 0.00179 -0.0853 0.2872 1.0000
2.750 0.7545 0.00755 0.00190 -0.0852 0.2659 1.0000
3.000 0.7809 0.00790 0.00205 -0.0851 0.2307 1.0000
3.250 0.8023 0.00919 0.00270 -0.0844 0.1014 1.0000
3.500 0.8278 0.00974 0.00303 -0.0841 0.0575 1.0000
3.750 0.8548 0.00997 0.00324 -0.0840 0.0510 1.0000
4.000 0.8820 0.01015 0.00341 -0.0839 0.0495 1.0000
4.250 0.9092 0.01032 0.00358 -0.0839 0.0485 1.0000
4.500 0.9363 0.01050 0.00378 -0.0838 0.0460 1.0000
4.750 0.9629 0.01075 0.00399 -0.0837 0.0410 1.0000
5.000 0.9899 0.01092 0.00414 -0.0836 0.0363 1.0000
5.250 1.0154 0.01134 0.00446 -0.0833 0.0150 1.0000
5.500 1.0414 0.01170 0.00487 -0.0831 0.0125 1.0000
5.750 1.0673 0.01206 0.00532 -0.0827 0.0108 1.0000
6.000 1.0928 0.01247 0.00578 -0.0824 0.0102 1.0000
6.250 1.1181 0.01288 0.00623 -0.0820 0.0096 1.0000
6.500 1.1427 0.01340 0.00680 -0.0815 0.0089 1.0000
6.750 1.1668 0.01397 0.00744 -0.0810 0.0082 1.0000
7.000 1.1902 0.01458 0.00811 -0.0804 0.0075 1.0000
7.250 1.2123 0.01537 0.00897 -0.0796 0.0072 1.0000
7.500 1.2318 0.01642 0.01011 -0.0784 0.0068 1.0000
7.750 1.2442 0.01824 0.01204 -0.0763 0.0065 1.0000
8.000 1.2635 0.01914 0.01301 -0.0751 0.0061 1.0000
8.250 1.2846 0.01980 0.01374 -0.0742 0.0058 1.0000
8.500 1.3016 0.02088 0.01490 -0.0727 0.0056 1.0000
8.750 1.3157 0.02225 0.01634 -0.0707 0.0055 1.0000
9.000 1.3277 0.02388 0.01804 -0.0685 0.0056 1.0000
9.250 1.3394 0.02578 0.02000 -0.0663 0.0058 1.0000
9.500 1.3543 0.02726 0.02155 -0.0646 0.0057 1.0000
9.750 1.3695 0.02852 0.02291 -0.0630 0.0055 1.0000
12.250 1.4098 0.05132 0.04726 -0.0416 0.0053 1.0000
12.500 1.4023 0.05435 0.05046 -0.0409 0.0050 1.0000
12.750 1.3936 0.05797 0.05424 -0.0408 0.0049 1.0000
13.000 1.3843 0.06189 0.05831 -0.0412 0.0048 1.0000
13.250 1.3737 0.06624 0.06281 -0.0421 0.0047 1.0000
13.500 1.3622 0.07093 0.06764 -0.0433 0.0046 1.0000
13.750 1.3488 0.07610 0.07297 -0.0451 0.0045 1.0000
14.000 1.3346 0.08165 0.07866 -0.0472 0.0045 1.0000
14.250 1.3191 0.08759 0.08475 -0.0498 0.0045 1.0000
14.500 1.3033 0.09393 0.09123 -0.0527 0.0045 1.0000
14.750 1.2870 0.10075 0.09819 -0.0562 0.0045 1.0000
15.000 1.2696 0.10815 0.10574 -0.0602 0.0045 1.0000
15.250 1.2532 0.11571 0.11344 -0.0644 0.0045 1.0000
15.500 1.2356 0.12401 0.12188 -0.0693 0.0045 1.0000
15.750 1.2193 0.13237 0.13036 -0.0743 0.0046 1.0000
16.000 1.2007 0.14182 0.13995 -0.0801 0.0046 1.0000
16.250 1.1837 0.15143 0.14968 -0.0861 0.0047 1.0000
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Polar data table (+)
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