GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Reynolds number: 50,000 Max Cl/Cd: 42.24 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe173-il-50000-n5.txt Download as CSV file: xf-goe173-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 173 (ALBATROS 6020) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2647 0.11285 0.10645 -0.0297 1.0000 0.0607
-8.000 -0.2713 0.11224 0.10599 -0.0297 1.0000 0.0611
-7.750 -0.2765 0.11146 0.10537 -0.0304 1.0000 0.0614
-7.500 -0.2785 0.11041 0.10445 -0.0322 1.0000 0.0616
-7.250 -0.2639 0.10250 0.09656 -0.0267 1.0000 0.0642
-7.000 -0.2626 0.09997 0.09412 -0.0254 1.0000 0.0668
-6.750 -0.2650 0.09814 0.09243 -0.0246 1.0000 0.0693
-6.500 -0.2699 0.09678 0.09120 -0.0240 1.0000 0.0716
-6.250 -0.2772 0.09606 0.09061 -0.0241 1.0000 0.0736
-6.000 -0.2841 0.09588 0.09054 -0.0257 1.0000 0.0748
-5.750 -0.2613 0.09107 0.08575 -0.0309 0.9924 0.0770
-5.500 -0.2397 0.08643 0.08110 -0.0323 0.9848 0.0825
-5.000 -0.1750 0.07818 0.07274 -0.0485 0.9628 0.0932
-4.750 -0.1418 0.07433 0.06878 -0.0548 0.9535 0.1019
-4.500 -0.1094 0.07024 0.06462 -0.0616 0.9424 0.1078
-4.250 -0.0696 0.06689 0.06111 -0.0703 0.9314 0.1208
-4.000 -0.0349 0.06309 0.05720 -0.0757 0.9233 0.1358
-3.750 -0.0004 0.05957 0.05355 -0.0808 0.9138 0.1504
-3.500 0.0333 0.05605 0.04989 -0.0851 0.9048 0.1652
-3.250 0.0680 0.05222 0.04599 -0.0888 0.8979 0.1815
-3.000 0.1393 0.04630 0.03927 -0.0997 0.8901 0.0879
-2.750 0.1890 0.04203 0.03452 -0.1052 0.8838 0.0735
-2.500 0.2268 0.03893 0.03110 -0.1083 0.8751 0.0700
-2.250 0.2730 0.03608 0.02766 -0.1124 0.8688 0.0730
-2.000 0.3100 0.03378 0.02489 -0.1145 0.8595 0.0727
-1.750 0.3522 0.03147 0.02204 -0.1171 0.8525 0.0723
-1.500 0.3893 0.02983 0.01983 -0.1184 0.8420 0.0765
-1.250 0.4236 0.02832 0.01802 -0.1192 0.8299 0.0791
-1.000 0.4586 0.02695 0.01625 -0.1196 0.8165 0.0800
-0.750 0.4914 0.02584 0.01477 -0.1195 0.8022 0.0815
-0.500 0.5234 0.02497 0.01352 -0.1191 0.7879 0.0837
-0.250 0.5534 0.02435 0.01259 -0.1186 0.7745 0.0886
0.000 0.5826 0.02383 0.01196 -0.1184 0.7622 0.0975
0.250 0.6118 0.02340 0.01132 -0.1179 0.7500 0.1043
0.500 0.6399 0.02303 0.01087 -0.1175 0.7371 0.1134
0.750 0.6670 0.02276 0.01056 -0.1169 0.7234 0.1327
1.000 0.6887 0.02071 0.01042 -0.1155 0.7100 1.0000
1.250 0.7152 0.02091 0.01016 -0.1146 0.6958 1.0000
1.500 0.7411 0.02110 0.01006 -0.1138 0.6812 1.0000
1.750 0.7668 0.02130 0.01002 -0.1130 0.6662 1.0000
2.000 0.7922 0.02150 0.01003 -0.1122 0.6509 1.0000
2.250 0.8175 0.02170 0.01005 -0.1114 0.6351 1.0000
2.500 0.8427 0.02190 0.01009 -0.1105 0.6189 1.0000
2.750 0.8669 0.02215 0.01023 -0.1096 0.6016 1.0000
3.000 0.8910 0.02242 0.01040 -0.1087 0.5837 1.0000
3.250 0.9152 0.02270 0.01057 -0.1078 0.5658 1.0000
3.500 0.9397 0.02299 0.01077 -0.1069 0.5482 1.0000
3.750 0.9642 0.02331 0.01098 -0.1061 0.5312 1.0000
4.000 0.9883 0.02370 0.01128 -0.1053 0.5144 1.0000
4.250 1.0120 0.02415 0.01167 -0.1046 0.4978 1.0000
4.500 1.0358 0.02463 0.01213 -0.1039 0.4825 1.0000
4.750 1.0598 0.02513 0.01258 -0.1032 0.4689 1.0000
5.000 1.0840 0.02566 0.01307 -0.1026 0.4569 1.0000
5.250 1.1076 0.02629 0.01378 -0.1020 0.4453 1.0000
5.500 1.1313 0.02693 0.01446 -0.1014 0.4352 1.0000
5.750 1.1560 0.02751 0.01503 -0.1009 0.4268 1.0000
6.000 1.1789 0.02826 0.01590 -0.1003 0.4176 1.0000
6.250 1.2031 0.02894 0.01668 -0.0999 0.4102 1.0000
6.500 1.2261 0.02973 0.01762 -0.0993 0.4029 1.0000
6.750 1.2514 0.03045 0.01841 -0.0990 0.3975 1.0000
7.000 1.2731 0.03143 0.01964 -0.0984 0.3913 1.0000
7.250 1.2972 0.03225 0.02066 -0.0980 0.3860 1.0000
7.500 1.3199 0.03320 0.02182 -0.0975 0.3807 1.0000
7.750 1.3408 0.03427 0.02316 -0.0968 0.3751 1.0000
8.000 1.3651 0.03517 0.02426 -0.0964 0.3707 1.0000
8.250 1.3846 0.03636 0.02582 -0.0955 0.3654 1.0000
8.500 1.4032 0.03676 0.02633 -0.0940 0.3524 1.0000
8.750 1.4175 0.03723 0.02692 -0.0919 0.3375 1.0000
9.000 1.4265 0.03778 0.02762 -0.0893 0.3202 1.0000
9.250 1.4327 0.03842 0.02840 -0.0863 0.3028 1.0000
9.500 1.4413 0.03929 0.02950 -0.0839 0.2902 1.0000
9.750 1.4464 0.04026 0.03070 -0.0811 0.2771 1.0000
10.000 1.4497 0.04133 0.03206 -0.0781 0.2649 1.0000
10.250 1.4425 0.04283 0.03379 -0.0744 0.2498 1.0000
10.500 1.4347 0.04481 0.03604 -0.0715 0.2335 1.0000
10.750 1.4229 0.04750 0.03895 -0.0693 0.2092 1.0000
11.000 1.4112 0.05092 0.04253 -0.0682 0.1589 1.0000
11.250 1.3881 0.05557 0.04650 -0.0674 0.1107 1.0000
11.500 1.3665 0.06116 0.05187 -0.0676 0.0835 1.0000
11.750 1.3455 0.06718 0.05784 -0.0684 0.0659 1.0000
12.000 1.3269 0.07325 0.06399 -0.0695 0.0579 1.0000
12.250 1.3091 0.07948 0.07035 -0.0710 0.0531 1.0000
12.500 1.2915 0.08590 0.07691 -0.0728 0.0502 1.0000
12.750 1.2754 0.09227 0.08343 -0.0747 0.0475 1.0000
13.000 1.2601 0.09864 0.08995 -0.0766 0.0452 1.0000
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Polar data table (+)
Polar graphs
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