GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 441 AIRFOIL (goe441-il) Reynolds number: 200,000 Max Cl/Cd: 67.03 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe441-il-200000.txt Download as CSV file: xf-goe441-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 441 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 0.1197 0.09487 0.09107 -0.1081 0.9047 0.0707
-8.750 0.1278 0.09263 0.08883 -0.1086 0.8944 0.0723
-8.500 0.1201 0.09059 0.08675 -0.1135 0.8846 0.0754
-8.250 0.1209 0.08743 0.08359 -0.1157 0.8739 0.0760
-8.000 0.1400 0.08466 0.08077 -0.1138 0.8675 0.0766
-7.750 0.1542 0.08249 0.07860 -0.1129 0.8577 0.0774
-7.500 0.1668 0.08032 0.07637 -0.1130 0.8499 0.0788
-7.250 0.1757 0.07825 0.07431 -0.1136 0.8391 0.0811
-7.000 0.1606 0.07479 0.07083 -0.1243 0.8281 0.0848
-6.750 0.1760 0.07251 0.06853 -0.1206 0.8184 0.0854
-6.500 0.1919 0.07049 0.06646 -0.1190 0.8088 0.0863
-6.250 0.2061 0.06850 0.06442 -0.1188 0.7978 0.0876
-6.000 0.2191 0.06636 0.06226 -0.1200 0.7858 0.0895
-5.500 0.2738 0.03870 0.03393 -0.1715 0.7660 0.0759
-5.250 0.2969 0.03699 0.03216 -0.1720 0.7532 0.0765
-5.000 0.3483 0.02452 0.01833 -0.1895 0.7414 0.0694
-4.750 0.3785 0.02290 0.01640 -0.1909 0.7248 0.0703
-4.500 0.4089 0.02148 0.01463 -0.1921 0.7067 0.0718
-4.250 0.4395 0.02029 0.01300 -0.1931 0.6871 0.0744
-4.000 0.4688 0.01934 0.01174 -0.1936 0.6669 0.0769
-3.750 0.4962 0.01895 0.01120 -0.1936 0.6475 0.0794
-3.500 0.5250 0.01841 0.01037 -0.1938 0.6298 0.0827
-3.250 0.5537 0.01786 0.00961 -0.1940 0.6145 0.0865
-3.000 0.5817 0.01772 0.00934 -0.1941 0.6016 0.0917
-2.750 0.6102 0.01740 0.00884 -0.1943 0.5909 0.0979
-2.500 0.6390 0.01728 0.00853 -0.1944 0.5811 0.1056
-2.250 0.6677 0.01699 0.00819 -0.1947 0.5733 0.1148
-2.000 0.6968 0.01675 0.00790 -0.1951 0.5659 0.1253
-1.750 0.7262 0.01667 0.00769 -0.1955 0.5596 0.1369
-1.500 0.7553 0.01675 0.00769 -0.1957 0.5537 0.1482
-1.250 0.7839 0.01674 0.00772 -0.1960 0.5476 0.1594
-1.000 0.8131 0.01683 0.00773 -0.1962 0.5421 0.1703
-0.750 0.8426 0.01705 0.00782 -0.1965 0.5372 0.1815
-0.500 0.8710 0.01705 0.00790 -0.1967 0.5324 0.1932
-0.250 0.9000 0.01709 0.00795 -0.1970 0.5278 0.2067
0.000 0.9297 0.01716 0.00801 -0.1975 0.5235 0.2250
0.250 0.9604 0.01728 0.00813 -0.1982 0.5192 0.2566
0.500 0.9890 0.01717 0.00833 -0.1986 0.5150 0.3166
0.750 1.0174 0.01725 0.00868 -0.1988 0.5108 0.4070
1.000 1.0457 0.01748 0.00897 -0.1988 0.5070 0.4726
1.250 1.0743 0.01778 0.00925 -0.1990 0.5033 0.5164
1.500 1.1027 0.01814 0.00961 -0.1991 0.4996 0.5521
1.750 1.1284 0.01828 0.00990 -0.1987 0.4958 0.5840
2.000 1.1549 0.01847 0.01019 -0.1985 0.4921 0.6182
2.250 1.1816 0.01866 0.01046 -0.1983 0.4885 0.6576
2.500 1.2087 0.01887 0.01072 -0.1981 0.4851 0.7055
2.750 1.2359 0.01920 0.01107 -0.1979 0.4817 0.7696
3.000 1.2536 0.01905 0.01121 -0.1957 0.4787 1.0000
3.250 1.2800 0.01937 0.01151 -0.1956 0.4750 1.0000
3.500 1.3070 0.01970 0.01178 -0.1956 0.4713 1.0000
3.750 1.3347 0.02003 0.01203 -0.1957 0.4678 1.0000
4.000 1.3636 0.02042 0.01230 -0.1961 0.4647 1.0000
4.250 1.3918 0.02097 0.01276 -0.1963 0.4615 1.0000
4.500 1.4147 0.02128 0.01315 -0.1956 0.4579 1.0000
4.750 1.4391 0.02162 0.01351 -0.1951 0.4542 1.0000
5.000 1.4648 0.02194 0.01382 -0.1949 0.4507 1.0000
5.250 1.4920 0.02226 0.01408 -0.1949 0.4476 1.0000
5.500 1.5211 0.02271 0.01442 -0.1953 0.4446 1.0000
5.750 1.5444 0.02320 0.01496 -0.1948 0.4415 1.0000
6.000 1.5655 0.02359 0.01545 -0.1938 0.4378 1.0000
6.250 1.5886 0.02395 0.01584 -0.1931 0.4342 1.0000
6.500 1.6136 0.02426 0.01613 -0.1928 0.4309 1.0000
6.750 1.6410 0.02459 0.01640 -0.1929 0.4280 1.0000
7.000 1.6698 0.02515 0.01689 -0.1933 0.4251 1.0000
7.250 1.6864 0.02563 0.01754 -0.1916 0.4218 1.0000
7.500 1.7055 0.02609 0.01811 -0.1904 0.4181 1.0000
7.750 1.7274 0.02645 0.01851 -0.1896 0.4146 1.0000
8.000 1.7525 0.02674 0.01876 -0.1893 0.4115 1.0000
8.250 1.7814 0.02708 0.01903 -0.1897 0.4086 1.0000
8.500 1.7984 0.02770 0.01977 -0.1882 0.4052 1.0000
8.750 1.8122 0.02829 0.02051 -0.1861 0.4015 1.0000
9.000 1.8304 0.02876 0.02104 -0.1848 0.3980 1.0000
9.250 1.8528 0.02910 0.02140 -0.1841 0.3949 1.0000
9.500 1.8805 0.02937 0.02161 -0.1843 0.3920 1.0000
9.750 1.8961 0.02997 0.02230 -0.1826 0.3882 1.0000
10.000 1.9000 0.03059 0.02309 -0.1790 0.3837 1.0000
10.250 1.9121 0.03083 0.02337 -0.1766 0.3793 1.0000
10.500 1.9352 0.03079 0.02324 -0.1758 0.3752 1.0000
10.750 1.9413 0.03144 0.02398 -0.1727 0.3711 1.0000
11.000 1.9384 0.03232 0.02503 -0.1683 0.3667 1.0000
11.250 1.9470 0.03285 0.02561 -0.1657 0.3625 1.0000
11.500 1.9662 0.03306 0.02578 -0.1646 0.3587 1.0000
11.750 1.9720 0.03396 0.02676 -0.1619 0.3546 1.0000
12.000 1.9662 0.03531 0.02830 -0.1579 0.3502 1.0000
12.250 1.9723 0.03614 0.02919 -0.1555 0.3457 1.0000
12.500 1.9907 0.03643 0.02941 -0.1544 0.3415 1.0000
12.750 1.9844 0.03818 0.03134 -0.1510 0.3371 1.0000
13.000 1.9798 0.03989 0.03320 -0.1480 0.3323 1.0000
13.250 1.9861 0.04094 0.03427 -0.1461 0.3276 1.0000
13.500 1.9918 0.04217 0.03553 -0.1442 0.3228 1.0000
13.750 1.9794 0.04482 0.03839 -0.1412 0.3175 1.0000
14.000 1.9797 0.04655 0.04017 -0.1394 0.3123 1.0000
14.250 1.9826 0.04821 0.04185 -0.1377 0.3071 1.0000
14.500 1.9682 0.05161 0.04545 -0.1355 0.3015 1.0000
14.750 1.9682 0.05374 0.04761 -0.1341 0.2959 1.0000
15.000 1.9629 0.05659 0.05056 -0.1327 0.2905 1.0000
15.250 1.9492 0.06054 0.05469 -0.1313 0.2849 1.0000
15.500 1.9521 0.06256 0.05664 -0.1304 0.2784 1.0000
15.750 1.9304 0.06785 0.06216 -0.1294 0.2727 1.0000
16.000 1.9199 0.07185 0.06624 -0.1288 0.2664 1.0000
16.250 1.9082 0.07614 0.07062 -0.1283 0.2602 1.0000
16.500 1.8880 0.08179 0.07641 -0.1282 0.2538 1.0000
16.750 1.8784 0.08597 0.08061 -0.1281 0.2467 1.0000
17.000 1.8536 0.09256 0.08739 -0.1285 0.2403 1.0000
17.250 1.8423 0.09714 0.09196 -0.1288 0.2325 1.0000
17.500 1.8166 0.10402 0.09901 -0.1297 0.2257 1.0000
17.750 1.7996 0.10956 0.10458 -0.1304 0.2167 1.0000
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