GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il) Reynolds number: 200,000 Max Cl/Cd: 74.88 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe222-il-200000.txt Download as CSV file: xf-goe222-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 222 (MVA H.33) 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
------ -------- --------- --------- -------- -------- --------
-11.500 0.1286 0.09917 0.09542 -0.1334 0.9239 0.1012
-11.250 -0.1384 0.06967 0.06573 -0.1503 0.9389 0.0639
-11.000 -0.1822 0.05919 0.05508 -0.1582 0.9253 0.0612
-10.750 -0.2289 0.05072 0.04636 -0.1655 0.9096 0.0597
-10.500 -0.2621 0.04373 0.03895 -0.1749 0.8944 0.0585
-10.250 -0.2527 0.03865 0.03332 -0.1822 0.8900 0.0579
-10.000 -0.2515 0.03671 0.03113 -0.1817 0.8798 0.0579
-9.750 -0.2276 0.03439 0.02854 -0.1841 0.8765 0.0586
-9.500 -0.1986 0.03233 0.02622 -0.1867 0.8743 0.0597
-9.250 -0.1844 0.03116 0.02486 -0.1861 0.8675 0.0604
-9.000 -0.1620 0.02980 0.02328 -0.1866 0.8630 0.0610
-8.750 -0.1327 0.02839 0.02166 -0.1880 0.8605 0.0617
-8.500 -0.1008 0.02715 0.02021 -0.1896 0.8586 0.0624
-8.250 -0.0690 0.02575 0.01870 -0.1910 0.8571 0.0637
-8.000 -0.0583 0.02532 0.01832 -0.1887 0.8500 0.0648
-7.750 -0.0323 0.02454 0.01755 -0.1889 0.8465 0.0662
-7.500 -0.0019 0.02373 0.01671 -0.1899 0.8443 0.0676
-7.250 0.0312 0.02289 0.01583 -0.1912 0.8424 0.0692
-7.000 0.0669 0.02204 0.01489 -0.1930 0.8407 0.0712
-6.750 0.0822 0.02178 0.01467 -0.1914 0.8336 0.0731
-6.500 0.1139 0.02098 0.01388 -0.1928 0.8296 0.0763
-6.250 0.1511 0.02014 0.01297 -0.1948 0.8268 0.0802
-6.000 0.1908 0.01917 0.01196 -0.1975 0.8243 0.0861
-5.750 0.2139 0.01885 0.01164 -0.1972 0.8178 0.0943
-5.500 0.2472 0.01786 0.01078 -0.1991 0.8133 0.1300
-5.250 0.2838 0.01698 0.01035 -0.2017 0.8103 0.2554
-5.000 0.3194 0.01709 0.01037 -0.2029 0.8079 0.2852
-4.750 0.3446 0.01751 0.01075 -0.2024 0.8036 0.3010
-4.500 0.3695 0.01786 0.01107 -0.2018 0.7989 0.3130
-4.250 0.4004 0.01808 0.01114 -0.2023 0.7954 0.3256
-4.000 0.4328 0.01818 0.01128 -0.2028 0.7927 0.3338
-3.750 0.4693 0.01818 0.01106 -0.2043 0.7902 0.3443
-3.500 0.4872 0.01859 0.01162 -0.2025 0.7843 0.3501
-3.250 0.5157 0.01875 0.01171 -0.2025 0.7798 0.3593
-3.000 0.5482 0.01873 0.01168 -0.2031 0.7763 0.3675
-2.750 0.5838 0.01881 0.01167 -0.2043 0.7734 0.3781
-2.500 0.6031 0.01907 0.01198 -0.2028 0.7674 0.3847
-2.250 0.6302 0.01916 0.01209 -0.2026 0.7626 0.3913
-2.000 0.6648 0.01901 0.01177 -0.2039 0.7588 0.3987
-1.750 0.6997 0.01876 0.01146 -0.2052 0.7554 0.4033
-1.500 0.7189 0.01889 0.01164 -0.2037 0.7487 0.4067
-1.250 0.7494 0.01874 0.01142 -0.2042 0.7435 0.4111
-1.000 0.7863 0.01851 0.01102 -0.2060 0.7394 0.4168
-0.750 0.8088 0.01852 0.01103 -0.2051 0.7326 0.4205
-0.500 0.8369 0.01839 0.01091 -0.2051 0.7264 0.4241
-0.250 0.8723 0.01820 0.01062 -0.2065 0.7218 0.4287
0.000 0.8947 0.01829 0.01070 -0.2056 0.7145 0.4336
0.250 0.9237 0.01818 0.01052 -0.2058 0.7079 0.4384
0.500 0.9591 0.01799 0.01027 -0.2072 0.7029 0.4429
0.750 0.9773 0.01808 0.01044 -0.2054 0.6939 0.4470
1.000 1.0093 0.01794 0.01019 -0.2062 0.6874 0.4525
1.250 1.0335 0.01793 0.01018 -0.2056 0.6792 0.4573
1.500 1.0601 0.01781 0.01008 -0.2053 0.6710 0.4622
1.750 1.0850 0.01777 0.01003 -0.2047 0.6621 0.4681
2.000 1.1109 0.01767 0.00985 -0.2042 0.6526 0.4741
2.250 1.1320 0.01760 0.00984 -0.2030 0.6420 0.4787
2.500 1.1596 0.01746 0.00965 -0.2028 0.6331 0.4847
2.750 1.1774 0.01753 0.00974 -0.2010 0.6209 0.4911
3.000 1.2003 0.01752 0.00973 -0.2001 0.6106 0.4973
3.250 1.2238 0.01753 0.00971 -0.1993 0.6005 0.5044
3.500 1.2438 0.01769 0.00985 -0.1979 0.5895 0.5120
3.750 1.2678 0.01774 0.00988 -0.1973 0.5802 0.5188
4.000 1.2884 0.01793 0.01003 -0.1960 0.5700 0.5271
4.250 1.3106 0.01812 0.01022 -0.1951 0.5610 0.5354
4.500 1.3336 0.01835 0.01041 -0.1944 0.5530 0.5458
4.750 1.3576 0.01860 0.01066 -0.1939 0.5459 0.5560
5.000 1.3779 0.01889 0.01096 -0.1927 0.5385 0.5678
5.250 1.4072 0.01913 0.01115 -0.1932 0.5320 0.5814
5.500 1.4221 0.01945 0.01158 -0.1911 0.5247 0.5945
5.750 1.4475 0.01971 0.01183 -0.1909 0.5180 0.6126
6.000 1.4687 0.02003 0.01223 -0.1900 0.5116 0.6339
6.250 1.4882 0.02033 0.01266 -0.1888 0.5054 0.6599
6.500 1.5164 0.02050 0.01291 -0.1891 0.5002 0.7066
6.750 1.5290 0.02042 0.01323 -0.1862 0.4956 1.0000
7.000 1.5471 0.02092 0.01373 -0.1849 0.4902 1.0000
7.250 1.5708 0.02134 0.01411 -0.1845 0.4851 1.0000
7.500 1.6008 0.02176 0.01444 -0.1852 0.4803 1.0000
7.750 1.6124 0.02234 0.01511 -0.1827 0.4751 1.0000
8.000 1.6307 0.02284 0.01563 -0.1814 0.4699 1.0000
8.250 1.6605 0.02322 0.01591 -0.1821 0.4646 1.0000
8.500 1.6695 0.02388 0.01668 -0.1793 0.4591 1.0000
8.750 1.6824 0.02448 0.01733 -0.1771 0.4533 1.0000
9.000 1.7075 0.02489 0.01767 -0.1770 0.4477 1.0000
9.250 1.7174 0.02561 0.01850 -0.1745 0.4422 1.0000
9.500 1.7269 0.02633 0.01930 -0.1719 0.4362 1.0000
9.750 1.7492 0.02677 0.01968 -0.1714 0.4302 1.0000
10.000 1.7529 0.02771 0.02074 -0.1680 0.4238 1.0000
10.250 1.7596 0.02854 0.02165 -0.1652 0.4168 1.0000
10.500 1.7762 0.02916 0.02223 -0.1639 0.4099 1.0000
10.750 1.7724 0.03044 0.02366 -0.1599 0.4021 1.0000
11.000 1.7882 0.03104 0.02416 -0.1584 0.3941 1.0000
11.250 1.7767 0.03282 0.02614 -0.1538 0.3850 1.0000
11.500 1.7829 0.03387 0.02715 -0.1514 0.3759 1.0000
11.750 1.7743 0.03583 0.02927 -0.1476 0.3656 1.0000
12.000 1.7732 0.03752 0.03098 -0.1448 0.3553 1.0000
12.250 1.7719 0.03932 0.03277 -0.1422 0.3446 1.0000
12.500 1.7676 0.04159 0.03513 -0.1396 0.3329 1.0000
12.750 1.7664 0.04372 0.03728 -0.1374 0.3219 1.0000
13.000 1.7660 0.04585 0.03937 -0.1354 0.3118 1.0000
13.250 1.7654 0.04820 0.04178 -0.1336 0.3013 1.0000
13.500 1.7662 0.05039 0.04396 -0.1319 0.2926 1.0000
13.750 1.7665 0.05271 0.04628 -0.1302 0.2840 1.0000
14.000 1.7687 0.05489 0.04846 -0.1288 0.2767 1.0000
14.250 1.7705 0.05714 0.05073 -0.1274 0.2697 1.0000
14.500 1.7748 0.05908 0.05264 -0.1260 0.2638 1.0000
14.750 1.7762 0.06149 0.05516 -0.1248 0.2576 1.0000
15.000 1.7791 0.06362 0.05725 -0.1235 0.2515 1.0000
15.250 1.7808 0.06600 0.05969 -0.1224 0.2458 1.0000
15.500 1.7813 0.06857 0.06234 -0.1213 0.2401 1.0000
15.750 1.7859 0.07049 0.06418 -0.1202 0.2342 1.0000
16.000 1.7823 0.07368 0.06755 -0.1193 0.2288 1.0000
16.250 1.7801 0.07664 0.07058 -0.1184 0.2231 1.0000
16.500 1.7840 0.07872 0.07260 -0.1175 0.2177 1.0000
16.750 1.7785 0.08232 0.07641 -0.1170 0.2128 1.0000
17.000 1.7753 0.08557 0.07975 -0.1164 0.2075 1.0000
17.250 1.7757 0.08821 0.08236 -0.1158 0.2021 1.0000
17.500 1.7677 0.09234 0.08672 -0.1157 0.1970 1.0000
17.750 1.7612 0.09618 0.09065 -0.1156 0.1910 1.0000
18.000 1.7539 0.10019 0.09475 -0.1157 0.1849 1.0000
18.250 1.7431 0.10492 0.09963 -0.1161 0.1775 1.0000
18.500 1.7314 0.10977 0.10459 -0.1167 0.1693 1.0000
18.750 1.7157 0.11533 0.11021 -0.1177 0.1591 1.0000
19.000 1.6966 0.12152 0.11648 -0.1190 0.1436 1.0000
19.250 1.6718 0.12853 0.12345 -0.1208 0.1234 1.0000
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