GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il) Reynolds number: 200,000 Max Cl/Cd: 87.55 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe225-il-200000.txt Download as CSV file: xf-goe225-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 225 (MVA H.35) 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
------ -------- --------- --------- -------- -------- --------
-8.500 0.0131 0.09400 0.09016 -0.1055 0.9450 0.0720
-8.250 0.0270 0.09109 0.08724 -0.1100 0.9421 0.0756
-8.000 -0.0067 0.09129 0.08751 -0.1131 0.9293 0.0772
-7.750 0.0172 0.08630 0.08250 -0.1143 0.9279 0.0781
-7.500 0.0472 0.08291 0.07909 -0.1153 0.9266 0.0792
-7.250 0.0706 0.08000 0.07615 -0.1173 0.9243 0.0808
-7.000 0.0645 0.07924 0.07543 -0.1144 0.9161 0.0819
-6.750 0.0738 0.07704 0.07323 -0.1160 0.9114 0.0841
-6.500 0.0669 0.07353 0.06972 -0.1328 0.8992 0.0884
-6.250 0.0786 0.07014 0.06635 -0.1296 0.8963 0.0892
-6.000 0.0998 0.06802 0.06422 -0.1278 0.8941 0.0903
-5.750 0.1747 0.03810 0.03361 -0.1816 0.8903 0.0654
-5.500 0.2561 0.02691 0.02102 -0.2045 0.8898 0.0633
-5.250 0.2734 0.02609 0.01996 -0.2038 0.8816 0.0646
-5.000 0.3148 0.02429 0.01775 -0.2072 0.8789 0.0666
-4.750 0.3556 0.02270 0.01583 -0.2099 0.8765 0.0682
-4.500 0.3933 0.02167 0.01479 -0.2118 0.8743 0.0706
-4.250 0.4255 0.02108 0.01410 -0.2125 0.8707 0.0737
-4.000 0.4516 0.02071 0.01357 -0.2122 0.8640 0.0776
-3.750 0.4856 0.02006 0.01299 -0.2132 0.8602 0.0837
-3.500 0.5221 0.01925 0.01213 -0.2145 0.8573 0.0937
-3.250 0.5537 0.01869 0.01156 -0.2151 0.8526 0.1108
-3.000 0.5814 0.01833 0.01120 -0.2151 0.8458 0.1266
-2.750 0.6148 0.01777 0.01062 -0.2159 0.8416 0.1401
-2.500 0.6494 0.01722 0.01002 -0.2167 0.8383 0.1514
-2.250 0.6738 0.01716 0.00997 -0.2160 0.8295 0.1621
-2.000 0.7058 0.01671 0.00956 -0.2164 0.8244 0.1767
-1.750 0.7396 0.01624 0.00909 -0.2170 0.8205 0.1923
-1.500 0.7647 0.01611 0.00905 -0.2163 0.8105 0.2088
-1.250 0.7973 0.01565 0.00866 -0.2166 0.8051 0.2388
-1.000 0.8247 0.01551 0.00860 -0.2162 0.7960 0.2857
-0.750 0.8550 0.01526 0.00834 -0.2161 0.7888 0.3216
-0.500 0.8821 0.01514 0.00825 -0.2156 0.7789 0.3449
-0.250 0.9121 0.01486 0.00793 -0.2154 0.7706 0.3641
0.000 0.9384 0.01473 0.00782 -0.2148 0.7583 0.3791
0.250 0.9665 0.01455 0.00760 -0.2144 0.7470 0.3935
0.500 0.9955 0.01434 0.00733 -0.2142 0.7356 0.4086
0.750 1.0221 0.01424 0.00724 -0.2136 0.7205 0.4230
1.000 1.0491 0.01416 0.00714 -0.2131 0.7051 0.4367
1.250 1.0763 0.01413 0.00705 -0.2127 0.6898 0.4511
1.500 1.1037 0.01415 0.00698 -0.2123 0.6747 0.4652
1.750 1.1307 0.01425 0.00700 -0.2120 0.6606 0.4815
2.000 1.1576 0.01440 0.00709 -0.2116 0.6477 0.4992
2.250 1.1847 0.01458 0.00719 -0.2113 0.6362 0.5176
2.500 1.2113 0.01478 0.00736 -0.2110 0.6250 0.5364
2.750 1.2377 0.01500 0.00757 -0.2107 0.6147 0.5565
3.000 1.2653 0.01524 0.00771 -0.2106 0.6054 0.5791
3.250 1.2902 0.01544 0.00797 -0.2100 0.5944 0.6022
3.500 1.3162 0.01566 0.00818 -0.2097 0.5842 0.6270
3.750 1.3416 0.01586 0.00838 -0.2092 0.5744 0.6545
4.000 1.3663 0.01603 0.00864 -0.2086 0.5659 0.6916
4.250 1.3859 0.01583 0.00876 -0.2067 0.5582 1.0000
4.500 1.4127 0.01622 0.00906 -0.2066 0.5505 1.0000
4.750 1.4379 0.01656 0.00938 -0.2062 0.5427 1.0000
5.000 1.4652 0.01698 0.00968 -0.2061 0.5358 1.0000
5.250 1.4887 0.01731 0.01006 -0.2054 0.5281 1.0000
5.500 1.5150 0.01770 0.01036 -0.2051 0.5211 1.0000
5.750 1.5383 0.01807 0.01078 -0.2044 0.5137 1.0000
6.000 1.5623 0.01843 0.01113 -0.2037 0.5065 1.0000
6.250 1.5875 0.01884 0.01151 -0.2033 0.4998 1.0000
6.500 1.6088 0.01919 0.01194 -0.2021 0.4918 1.0000
6.750 1.6344 0.01959 0.01225 -0.2018 0.4848 1.0000
7.000 1.6529 0.01994 0.01274 -0.2001 0.4765 1.0000
7.250 1.6754 0.02030 0.01306 -0.1992 0.4686 1.0000
7.500 1.6925 0.02067 0.01354 -0.1973 0.4594 1.0000
7.750 1.7126 0.02103 0.01383 -0.1959 0.4504 1.0000
8.000 1.7255 0.02141 0.01435 -0.1933 0.4401 1.0000
8.250 1.7420 0.02183 0.01476 -0.1913 0.4309 1.0000
8.500 1.7529 0.02226 0.01528 -0.1883 0.4205 1.0000
8.750 1.7619 0.02276 0.01582 -0.1850 0.4102 1.0000
9.000 1.7710 0.02334 0.01636 -0.1818 0.3998 1.0000
9.250 1.7773 0.02403 0.01714 -0.1783 0.3876 1.0000
9.500 1.7852 0.02480 0.01797 -0.1752 0.3756 1.0000
9.750 1.7927 0.02568 0.01884 -0.1723 0.3638 1.0000
10.000 1.7990 0.02669 0.01983 -0.1692 0.3513 1.0000
10.250 1.8051 0.02779 0.02097 -0.1664 0.3379 1.0000
10.500 1.8107 0.02900 0.02220 -0.1636 0.3245 1.0000
10.750 1.8156 0.03032 0.02352 -0.1608 0.3115 1.0000
11.000 1.8198 0.03177 0.02495 -0.1581 0.2991 1.0000
11.500 1.8267 0.03493 0.02811 -0.1528 0.2749 1.0000
11.750 1.8304 0.03659 0.02980 -0.1504 0.2640 1.0000
12.000 1.8326 0.03840 0.03159 -0.1480 0.2546 1.0000
12.250 1.8365 0.04015 0.03340 -0.1458 0.2448 1.0000
12.500 1.8387 0.04205 0.03535 -0.1435 0.2360 1.0000
12.750 1.8393 0.04417 0.03749 -0.1413 0.2269 1.0000
13.000 1.8415 0.04624 0.03965 -0.1394 0.2175 1.0000
13.250 1.8391 0.04879 0.04222 -0.1373 0.2076 1.0000
13.500 1.8362 0.05151 0.04500 -0.1354 0.1964 1.0000
13.750 1.8324 0.05448 0.04803 -0.1336 0.1835 1.0000
14.000 1.8251 0.05797 0.05154 -0.1320 0.1685 1.0000
14.250 1.8128 0.06219 0.05575 -0.1304 0.1509 1.0000
14.500 1.7968 0.06709 0.06059 -0.1291 0.1261 1.0000
14.750 1.7739 0.07305 0.06642 -0.1281 0.0996 1.0000
15.000 1.7504 0.07931 0.07256 -0.1275 0.0819 1.0000
15.250 1.7303 0.08528 0.07851 -0.1272 0.0735 1.0000
15.500 1.7122 0.09116 0.08443 -0.1271 0.0684 1.0000
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Polar data table (+)
Polar graphs
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