GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 100,000 Max Cl/Cd: 55.98 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe176-il-100000.txt Download as CSV file: xf-goe176-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 176 (ALBATROS 7020) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2954 0.09642 0.09208 -0.0278 1.0000 0.1076
-7.250 -0.3215 0.09683 0.09271 -0.0302 1.0000 0.1091
-7.000 -0.3232 0.09327 0.08926 -0.0287 1.0000 0.1104
-6.750 -0.3103 0.08979 0.08578 -0.0234 1.0000 0.1132
-6.500 -0.3158 0.08824 0.08433 -0.0209 1.0000 0.1158
-6.250 -0.3278 0.08716 0.08336 -0.0188 1.0000 0.1184
-5.750 -0.3528 0.08418 0.08056 -0.0250 1.0000 0.1244
-5.250 -0.2782 0.07416 0.07046 -0.0378 0.9855 0.1398
-5.000 -0.2316 0.06897 0.06517 -0.0497 0.9755 0.1530
-4.750 -0.1422 0.04227 0.03726 -0.0877 0.9705 0.0819
-4.500 -0.0852 0.03196 0.02562 -0.0986 0.9654 0.0692
-4.250 -0.0326 0.02754 0.02048 -0.1045 0.9606 0.0685
-4.000 0.0111 0.02481 0.01738 -0.1081 0.9515 0.0726
-3.750 0.0585 0.02283 0.01507 -0.1117 0.9441 0.0768
-3.500 0.1054 0.02112 0.01313 -0.1149 0.9358 0.0843
-3.250 0.1501 0.01978 0.01175 -0.1177 0.9262 0.0976
-3.000 0.2008 0.01835 0.01054 -0.1217 0.9202 0.1393
-2.750 0.2414 0.01918 0.01155 -0.1232 0.9084 0.2500
-2.500 0.2806 0.01944 0.01168 -0.1248 0.8973 0.2873
-2.250 0.3212 0.01928 0.01149 -0.1267 0.8872 0.3170
-2.000 0.3578 0.01898 0.01120 -0.1278 0.8751 0.3410
-1.750 0.3918 0.01852 0.01060 -0.1284 0.8610 0.3542
-1.500 0.4245 0.01811 0.01004 -0.1288 0.8462 0.3657
-1.250 0.4556 0.01781 0.00956 -0.1289 0.8309 0.3771
-1.000 0.4846 0.01756 0.00924 -0.1286 0.8162 0.3885
-0.750 0.5128 0.01736 0.00898 -0.1282 0.8020 0.4005
-0.500 0.5405 0.01720 0.00875 -0.1278 0.7877 0.4128
-0.250 0.5681 0.01705 0.00854 -0.1273 0.7734 0.4262
0.000 0.5952 0.01690 0.00835 -0.1267 0.7589 0.4403
0.250 0.6218 0.01674 0.00817 -0.1259 0.7440 0.4559
0.500 0.6483 0.01656 0.00799 -0.1251 0.7285 0.4757
0.750 0.6748 0.01635 0.00779 -0.1243 0.7123 0.5016
1.000 0.7008 0.01600 0.00758 -0.1234 0.6955 0.5458
1.250 0.7222 0.01491 0.00731 -0.1210 0.6785 1.0000
1.500 0.7494 0.01508 0.00717 -0.1204 0.6591 1.0000
1.750 0.7752 0.01527 0.00715 -0.1195 0.6371 1.0000
2.000 0.8015 0.01550 0.00712 -0.1187 0.6156 1.0000
2.250 0.8265 0.01582 0.00727 -0.1178 0.5912 1.0000
2.500 0.8527 0.01620 0.00738 -0.1171 0.5708 1.0000
2.750 0.8779 0.01664 0.00768 -0.1164 0.5503 1.0000
3.000 0.9038 0.01708 0.00801 -0.1159 0.5338 1.0000
3.250 0.9299 0.01753 0.00833 -0.1155 0.5200 1.0000
3.500 0.9561 0.01795 0.00862 -0.1150 0.5076 1.0000
3.750 0.9820 0.01832 0.00888 -0.1145 0.4955 1.0000
4.000 1.0069 0.01866 0.00923 -0.1139 0.4828 1.0000
4.250 1.0318 0.01899 0.00954 -0.1133 0.4711 1.0000
4.500 1.0571 0.01932 0.00982 -0.1128 0.4607 1.0000
4.750 1.0825 0.01964 0.01008 -0.1122 0.4510 1.0000
5.000 1.1071 0.02000 0.01053 -0.1116 0.4413 1.0000
5.250 1.1324 0.02034 0.01083 -0.1111 0.4327 1.0000
5.500 1.1572 0.02072 0.01126 -0.1106 0.4242 1.0000
5.750 1.1826 0.02115 0.01174 -0.1101 0.4175 1.0000
6.000 1.2073 0.02157 0.01221 -0.1096 0.4097 1.0000
6.250 1.2321 0.02201 0.01269 -0.1091 0.4024 1.0000
6.500 1.2567 0.02246 0.01322 -0.1085 0.3952 1.0000
6.750 1.2817 0.02298 0.01380 -0.1081 0.3889 1.0000
7.000 1.3055 0.02349 0.01443 -0.1074 0.3816 1.0000
7.250 1.3304 0.02403 0.01500 -0.1069 0.3747 1.0000
7.500 1.3532 0.02459 0.01570 -0.1062 0.3667 1.0000
7.750 1.3774 0.02519 0.01638 -0.1056 0.3593 1.0000
8.000 1.3998 0.02576 0.01707 -0.1047 0.3505 1.0000
8.250 1.4205 0.02634 0.01778 -0.1036 0.3401 1.0000
8.500 1.4400 0.02682 0.01830 -0.1023 0.3268 1.0000
8.750 1.4581 0.02727 0.01882 -0.1008 0.3130 1.0000
9.000 1.4776 0.02774 0.01932 -0.0995 0.3013 1.0000
9.250 1.4927 0.02823 0.02013 -0.0975 0.2904 1.0000
9.500 1.5080 0.02867 0.02080 -0.0956 0.2790 1.0000
9.750 1.5200 0.02899 0.02134 -0.0932 0.2646 1.0000
10.000 1.5318 0.02938 0.02200 -0.0907 0.2495 1.0000
10.250 1.5437 0.02986 0.02274 -0.0884 0.2333 1.0000
10.500 1.5528 0.03045 0.02351 -0.0857 0.2110 1.0000
10.750 1.5500 0.03151 0.02440 -0.0816 0.1799 1.0000
11.000 1.5397 0.03356 0.02620 -0.0774 0.1536 1.0000
11.250 1.5286 0.03618 0.02872 -0.0738 0.1320 1.0000
11.750 1.5022 0.04291 0.03537 -0.0687 0.0793 1.0000
12.000 1.4828 0.04741 0.03976 -0.0674 0.0703 1.0000
12.250 1.4626 0.05246 0.04484 -0.0669 0.0661 1.0000
12.500 1.4410 0.05809 0.05052 -0.0672 0.0633 1.0000
12.750 1.4222 0.06372 0.05633 -0.0678 0.0607 1.0000
13.000 1.4034 0.06953 0.06229 -0.0687 0.0585 1.0000
13.250 1.3854 0.07528 0.06815 -0.0696 0.0566 1.0000
13.500 1.3699 0.08042 0.07331 -0.0699 0.0544 1.0000
13.750 1.3654 0.08365 0.07656 -0.0688 0.0511 1.0000
14.000 1.3648 0.08666 0.07965 -0.0680 0.0479 1.0000
14.250 1.3691 0.08850 0.08144 -0.0661 0.0445 1.0000
14.500 1.3786 0.08981 0.08272 -0.0636 0.0415 1.0000
14.750 1.3817 0.09278 0.08588 -0.0633 0.0398 1.0000
15.000 1.3881 0.09520 0.08845 -0.0623 0.0383 1.0000
15.250 1.3933 0.09790 0.09130 -0.0615 0.0372 1.0000
15.500 1.3976 0.10083 0.09435 -0.0610 0.0362 1.0000
15.750 1.4019 0.10386 0.09751 -0.0605 0.0354 1.0000
16.000 1.4075 0.10682 0.10057 -0.0598 0.0347 1.0000
16.250 1.4171 0.10981 0.10359 -0.0583 0.0338 1.0000
16.500 1.4038 0.11553 0.10957 -0.0609 0.0337 1.0000
16.750 1.3909 0.12150 0.11579 -0.0638 0.0336 1.0000
17.000 1.3768 0.12793 0.12245 -0.0673 0.0336 1.0000
17.250 1.3618 0.13480 0.12954 -0.0715 0.0336 1.0000
17.500 1.3463 0.14211 0.13706 -0.0761 0.0337 1.0000
17.750 1.3315 0.14966 0.14480 -0.0809 0.0338 1.0000
18.000 0.8975 0.17232 0.16847 -0.0806 0.0517 1.0000
18.250 0.8794 0.18084 0.17696 -0.0840 0.0526 1.0000
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