GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il) Reynolds number: 50,000 Max Cl/Cd: 29.21 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe182-il-50000.txt Download as CSV file: xf-goe182-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 182 (MVA H.27) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2870 0.09837 0.09201 -0.0161 1.0000 0.1850
-7.000 -0.3025 0.09979 0.09363 -0.0209 1.0000 0.1891
-6.750 -0.2808 0.09317 0.08702 -0.0159 1.0000 0.1965
-6.500 -0.2877 0.09295 0.08694 -0.0188 1.0000 0.2044
-6.250 -0.2781 0.08868 0.08276 -0.0163 1.0000 0.2101
-6.000 -0.2787 0.08732 0.08150 -0.0172 1.0000 0.2195
-5.750 -0.2767 0.08451 0.07882 -0.0166 1.0000 0.2246
-5.500 -0.2737 0.08229 0.07669 -0.0152 1.0000 0.2335
-5.250 -0.2767 0.08059 0.07512 -0.0161 1.0000 0.2400
-5.000 -0.2758 0.07830 0.07291 -0.0132 1.0000 0.2478
-4.750 -0.2800 0.07700 0.07170 -0.0144 1.0000 0.2559
-4.500 -0.2815 0.07501 0.06981 -0.0113 1.0000 0.2643
-4.250 -0.2828 0.07327 0.06815 -0.0113 1.0000 0.2738
-4.000 -0.2805 0.07177 0.06669 -0.0125 1.0000 0.2875
-3.750 -0.2764 0.07011 0.06508 -0.0130 1.0000 0.3026
-3.500 -0.2714 0.06827 0.06329 -0.0129 1.0000 0.3183
-3.250 -0.2658 0.06630 0.06138 -0.0126 1.0000 0.3344
-3.000 -0.2441 0.06326 0.05837 -0.0133 0.9942 0.3559
-2.750 -0.1953 0.05953 0.05460 -0.0192 0.9774 0.4037
-2.500 -0.1595 0.05618 0.05129 -0.0201 0.9606 0.4684
-2.000 0.1417 0.04049 0.03309 -0.0922 0.9235 0.2043
-1.750 0.2100 0.03655 0.02839 -0.1004 0.9051 0.1884
-1.500 0.2720 0.03357 0.02494 -0.1062 0.8862 0.1866
-1.250 0.3266 0.03130 0.02235 -0.1100 0.8665 0.1957
-1.000 0.3798 0.02921 0.01968 -0.1127 0.8474 0.2051
-0.750 0.4160 0.02790 0.01828 -0.1127 0.8232 0.2237
-0.500 0.4559 0.02653 0.01669 -0.1126 0.8014 0.2516
-0.250 0.4883 0.02548 0.01559 -0.1115 0.7761 0.2947
0.000 0.5199 0.02402 0.01446 -0.1099 0.7530 0.4017
0.250 0.5471 0.02174 0.01336 -0.1075 0.7274 1.0000
0.500 0.5754 0.02201 0.01298 -0.1059 0.7026 1.0000
0.750 0.6002 0.02250 0.01309 -0.1044 0.6754 1.0000
1.000 0.6255 0.02298 0.01322 -0.1031 0.6512 1.0000
1.250 0.6507 0.02350 0.01345 -0.1019 0.6286 1.0000
1.500 0.6767 0.02397 0.01361 -0.1007 0.6095 1.0000
1.750 0.7026 0.02448 0.01384 -0.0998 0.5922 1.0000
2.000 0.7282 0.02509 0.01424 -0.0989 0.5760 1.0000
2.250 0.7536 0.02580 0.01478 -0.0983 0.5613 1.0000
2.500 0.7783 0.02670 0.01559 -0.0979 0.5480 1.0000
2.750 0.8029 0.02771 0.01653 -0.0975 0.5368 1.0000
3.000 0.8299 0.02841 0.01703 -0.0970 0.5287 1.0000
3.250 0.8523 0.02977 0.01848 -0.0969 0.5186 1.0000
3.500 0.8782 0.03066 0.01925 -0.0964 0.5117 1.0000
3.750 0.8993 0.03222 0.02094 -0.0963 0.5034 1.0000
4.000 0.9255 0.03308 0.02170 -0.0959 0.4978 1.0000
4.250 0.9437 0.03514 0.02394 -0.0960 0.4913 1.0000
4.500 0.9641 0.03692 0.02582 -0.0959 0.4864 1.0000
4.750 0.9874 0.03835 0.02728 -0.0957 0.4828 1.0000
5.000 1.0063 0.04048 0.02951 -0.0958 0.4797 1.0000
5.250 1.0125 0.04438 0.03369 -0.0965 0.4765 1.0000
5.500 1.0151 0.04876 0.03828 -0.0973 0.4742 1.0000
5.750 1.0107 0.05401 0.04371 -0.0985 0.4724 1.0000
6.000 0.9817 0.06249 0.05234 -0.1013 0.4732 1.0000
6.250 0.9560 0.07043 0.06033 -0.1041 0.4782 1.0000
6.500 0.9691 0.07394 0.06389 -0.1048 0.4809 1.0000
6.750 0.7549 0.09987 0.08997 -0.1218 0.6587 1.0000
7.000 0.7684 0.10285 0.09295 -0.1219 0.6533 1.0000
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Polar data table (+)
Polar graphs
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