GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 177 AIRFOIL (goe177-il) Reynolds number: 500,000 Max Cl/Cd: 91.21 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe177-il-500000.txt Download as CSV file: xf-goe177-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3262 0.08645 0.08444 -0.0192 1.0000 0.0141
-7.000 -0.3237 0.08387 0.08190 -0.0198 1.0000 0.0144
-6.750 -0.3208 0.08120 0.07927 -0.0209 1.0000 0.0148
-6.500 -0.3187 0.07858 0.07668 -0.0216 1.0000 0.0152
-6.250 -0.3169 0.07594 0.07407 -0.0223 1.0000 0.0158
-6.000 -0.2819 0.07034 0.06844 -0.0327 0.9959 0.0175
-5.750 -0.2317 0.06441 0.06243 -0.0463 0.9904 0.0187
-5.500 -0.1904 0.05824 0.05619 -0.0564 0.9856 0.0188
-5.250 -0.1611 0.05086 0.04874 -0.0649 0.9806 0.0204
-5.000 -0.1299 0.04849 0.04633 -0.0686 0.9727 0.0225
-4.750 -0.0907 0.04369 0.04139 -0.0754 0.9627 0.0253
-4.250 -0.0098 0.02252 0.01920 -0.0897 0.9380 0.0177
-4.000 0.0198 0.01531 0.01091 -0.0912 0.9200 0.0164
-3.750 0.0470 0.01336 0.00848 -0.0907 0.8929 0.0171
-3.500 0.0731 0.01234 0.00708 -0.0898 0.8572 0.0181
-3.250 0.0990 0.01174 0.00613 -0.0889 0.8188 0.0190
-3.000 0.1251 0.01045 0.00447 -0.0884 0.7871 0.0220
-2.500 0.1795 0.00972 0.00331 -0.0875 0.7359 0.0273
-2.250 0.2070 0.00923 0.00267 -0.0873 0.7149 0.0358
-2.000 0.2348 0.00907 0.00250 -0.0870 0.6943 0.0584
-1.750 0.2624 0.00929 0.00260 -0.0868 0.6749 0.0746
-1.500 0.2899 0.00929 0.00250 -0.0867 0.6556 0.0850
-1.250 0.3175 0.00927 0.00236 -0.0865 0.6364 0.0924
-1.000 0.3449 0.00926 0.00226 -0.0864 0.6174 0.0995
-0.750 0.3726 0.00927 0.00216 -0.0863 0.5987 0.1032
-0.500 0.4002 0.00915 0.00198 -0.0862 0.5810 0.1088
-0.250 0.4279 0.00915 0.00190 -0.0861 0.5654 0.1144
0.000 0.4555 0.00917 0.00180 -0.0860 0.5472 0.1184
0.250 0.4830 0.00915 0.00173 -0.0859 0.5250 0.1266
0.500 0.5104 0.00917 0.00168 -0.0858 0.5001 0.1440
0.750 0.5377 0.00895 0.00174 -0.0859 0.4783 0.2756
1.000 0.5650 0.00867 0.00181 -0.0861 0.4619 0.4388
1.500 0.6137 0.00766 0.00187 -0.0844 0.4311 1.0000
1.750 0.6412 0.00782 0.00191 -0.0843 0.4151 1.0000
2.000 0.6686 0.00800 0.00196 -0.0842 0.3991 1.0000
2.250 0.6959 0.00817 0.00204 -0.0841 0.3837 1.0000
2.500 0.7231 0.00836 0.00213 -0.0840 0.3691 1.0000
2.750 0.7504 0.00854 0.00222 -0.0839 0.3554 1.0000
3.000 0.7776 0.00873 0.00233 -0.0838 0.3428 1.0000
3.250 0.8047 0.00892 0.00245 -0.0838 0.3302 1.0000
3.500 0.8318 0.00912 0.00259 -0.0837 0.3172 1.0000
3.750 0.8581 0.00941 0.00275 -0.0835 0.2946 1.0000
4.000 0.8845 0.00971 0.00291 -0.0834 0.2681 1.0000
4.250 0.9088 0.01034 0.00319 -0.0830 0.2077 1.0000
4.500 0.9290 0.01167 0.00398 -0.0823 0.1022 1.0000
4.750 0.9533 0.01230 0.00442 -0.0819 0.0608 1.0000
5.000 0.9790 0.01269 0.00479 -0.0816 0.0549 1.0000
5.250 1.0050 0.01298 0.00509 -0.0814 0.0485 1.0000
5.500 1.0309 0.01328 0.00538 -0.0812 0.0411 1.0000
5.750 1.0564 0.01366 0.00565 -0.0809 0.0219 1.0000
6.000 1.0816 0.01407 0.00604 -0.0805 0.0165 1.0000
6.250 1.1068 0.01447 0.00653 -0.0801 0.0153 1.0000
6.500 1.1315 0.01495 0.00711 -0.0796 0.0144 1.0000
6.750 1.1555 0.01552 0.00780 -0.0790 0.0136 1.0000
7.000 1.1787 0.01618 0.00860 -0.0783 0.0131 1.0000
7.250 1.2007 0.01698 0.00951 -0.0774 0.0126 1.0000
7.500 1.2192 0.01816 0.01082 -0.0761 0.0116 1.0000
7.750 1.2353 0.01952 0.01230 -0.0745 0.0111 1.0000
8.000 1.2496 0.02097 0.01385 -0.0727 0.0109 1.0000
8.250 1.2618 0.02253 0.01552 -0.0706 0.0107 1.0000
8.500 1.2740 0.02406 0.01715 -0.0684 0.0107 1.0000
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Polar data table (+)
Polar graphs
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