GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 439 AIRFOIL (goe439-il) Reynolds number: 500,000 Max Cl/Cd: 108.36 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe439-il-500000.txt Download as CSV file: xf-goe439-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 439 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2963 0.09118 0.08908 -0.0291 1.0000 0.0151
-7.750 -0.2992 0.08912 0.08707 -0.0280 1.0000 0.0152
-7.500 -0.3058 0.08753 0.08553 -0.0260 1.0000 0.0155
-7.250 -0.3017 0.08491 0.08295 -0.0274 0.9982 0.0158
-7.000 -0.2774 0.08053 0.07857 -0.0345 0.9927 0.0174
-6.750 -0.2378 0.07456 0.07257 -0.0499 0.9852 0.0191
-6.500 -0.1409 0.04838 0.04647 -0.0657 0.9634 0.0199
-6.250 -0.1190 0.04447 0.04253 -0.0693 0.9566 0.0205
-6.000 -0.0980 0.04045 0.03847 -0.0738 0.9439 0.0210
-5.750 -0.0776 0.03644 0.03439 -0.0783 0.9292 0.0219
-5.500 -0.0586 0.03243 0.03029 -0.0825 0.9114 0.0231
-5.250 -0.0377 0.02809 0.02582 -0.0870 0.8940 0.0247
-5.000 -0.0073 0.02401 0.02150 -0.0921 0.8794 0.0264
-4.750 0.0150 0.01952 0.01676 -0.0948 0.8656 0.0265
-4.500 0.0358 0.02120 0.01746 -0.1062 0.8924 0.0186
-4.250 0.0601 0.01764 0.01321 -0.1060 0.8770 0.0195
-4.000 0.0836 0.01446 0.00941 -0.1055 0.8623 0.0198
-3.750 0.1086 0.01281 0.00743 -0.1049 0.8480 0.0210
-3.500 0.1348 0.01214 0.00657 -0.1044 0.8343 0.0223
-3.250 0.1612 0.01153 0.00576 -0.1039 0.8210 0.0242
-3.000 0.1881 0.01144 0.00552 -0.1034 0.8083 0.0264
-2.750 0.2134 0.01026 0.00415 -0.1028 0.7965 0.0298
-2.500 0.2399 0.00997 0.00374 -0.1023 0.7846 0.0333
-2.250 0.2663 0.00968 0.00333 -0.1018 0.7729 0.0375
-2.000 0.2923 0.00924 0.00284 -0.1014 0.7613 0.0439
-1.750 0.3191 0.00912 0.00262 -0.1010 0.7501 0.0484
-1.500 0.3451 0.00877 0.00221 -0.1005 0.7389 0.0569
-1.250 0.3716 0.00861 0.00198 -0.1001 0.7277 0.0655
-1.000 0.3981 0.00848 0.00189 -0.0997 0.7158 0.0853
-0.750 0.4249 0.00844 0.00186 -0.0993 0.7036 0.1170
-0.500 0.4515 0.00840 0.00180 -0.0990 0.6912 0.1339
-0.250 0.4780 0.00838 0.00174 -0.0986 0.6782 0.1457
0.000 0.5045 0.00835 0.00168 -0.0982 0.6645 0.1578
0.250 0.5307 0.00830 0.00163 -0.0979 0.6500 0.1761
0.500 0.5563 0.00811 0.00163 -0.0975 0.6346 0.2543
0.750 0.5937 0.00651 0.00173 -0.0999 0.6178 1.0000
1.000 0.6192 0.00664 0.00172 -0.0993 0.6011 1.0000
1.250 0.6447 0.00678 0.00174 -0.0988 0.5843 1.0000
1.500 0.6702 0.00692 0.00177 -0.0982 0.5680 1.0000
1.750 0.6957 0.00707 0.00181 -0.0977 0.5525 1.0000
2.000 0.7213 0.00724 0.00188 -0.0972 0.5375 1.0000
2.250 0.7468 0.00741 0.00196 -0.0967 0.5228 1.0000
2.500 0.7722 0.00758 0.00205 -0.0962 0.5082 1.0000
2.750 0.7977 0.00776 0.00215 -0.0957 0.4934 1.0000
3.000 0.8233 0.00793 0.00226 -0.0953 0.4807 1.0000
3.250 0.8488 0.00811 0.00239 -0.0948 0.4692 1.0000
3.500 0.8744 0.00830 0.00252 -0.0944 0.4576 1.0000
3.750 0.9001 0.00846 0.00266 -0.0940 0.4461 1.0000
4.000 0.9258 0.00863 0.00281 -0.0936 0.4349 1.0000
4.250 0.9510 0.00883 0.00298 -0.0931 0.4212 1.0000
4.500 0.9761 0.00904 0.00314 -0.0926 0.4070 1.0000
4.750 1.0012 0.00924 0.00332 -0.0921 0.3942 1.0000
5.000 1.0258 0.00948 0.00350 -0.0916 0.3768 1.0000
5.250 1.0500 0.00975 0.00372 -0.0910 0.3586 1.0000
5.500 1.0744 0.01001 0.00394 -0.0905 0.3417 1.0000
5.750 1.0985 0.01030 0.00417 -0.0899 0.3218 1.0000
6.000 1.1218 0.01065 0.00445 -0.0892 0.3001 1.0000
6.250 1.1435 0.01115 0.00479 -0.0883 0.2625 1.0000
6.500 1.1593 0.01221 0.00539 -0.0866 0.1841 1.0000
6.750 1.1604 0.01477 0.00701 -0.0827 0.0346 1.0000
7.000 1.1800 0.01548 0.00780 -0.0814 0.0265 1.0000
7.250 1.1984 0.01630 0.00874 -0.0798 0.0221 1.0000
7.500 1.2182 0.01692 0.00945 -0.0785 0.0202 1.0000
7.750 1.2361 0.01767 0.01030 -0.0769 0.0185 1.0000
8.000 1.2511 0.01859 0.01131 -0.0750 0.0170 1.0000
8.250 1.2567 0.02014 0.01299 -0.0716 0.0157 1.0000
8.500 1.2675 0.02117 0.01411 -0.0690 0.0149 1.0000
8.750 1.2792 0.02194 0.01496 -0.0665 0.0142 1.0000
9.000 1.2858 0.02298 0.01608 -0.0633 0.0136 1.0000
9.250 1.2911 0.02415 0.01733 -0.0601 0.0132 1.0000
9.500 1.2965 0.02539 0.01867 -0.0572 0.0127 1.0000
9.750 1.3021 0.02671 0.02007 -0.0545 0.0123 1.0000
10.000 1.3068 0.02820 0.02163 -0.0520 0.0118 1.0000
10.250 1.3115 0.02984 0.02334 -0.0497 0.0115 1.0000
10.500 1.3165 0.03165 0.02522 -0.0476 0.0112 1.0000
10.750 1.3230 0.03417 0.02776 -0.0457 0.0107 1.0000
11.000 1.3377 0.03682 0.03053 -0.0444 0.0102 1.0000
11.250 1.3457 0.03834 0.03220 -0.0428 0.0100 1.0000
11.500 1.3548 0.04021 0.03424 -0.0413 0.0097 1.0000
11.750 1.3653 0.04250 0.03668 -0.0400 0.0096 1.0000
12.000 1.3750 0.04527 0.03964 -0.0387 0.0095 1.0000
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Polar data table (+)
Polar graphs
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