GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il) Reynolds number: 50,000 Max Cl/Cd: 5.02 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe223-il-50000.txt Download as CSV file: xf-goe223-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 223 (MVA H.34) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3020 0.12730 0.12209 -0.0237 0.9795 0.3155
-7.500 -0.3992 0.11106 0.10596 -0.0368 0.9734 0.1861
-7.250 -0.4787 0.09493 0.08996 -0.0501 0.9670 0.1571
-7.000 -0.5190 0.07290 0.06734 -0.0760 0.9606 0.1405
-6.750 -0.4907 0.06483 0.05869 -0.0870 0.9513 0.1357
-6.500 -0.4473 0.05805 0.05095 -0.0983 0.9418 0.1323
-6.250 -0.4119 0.05512 0.04754 -0.1030 0.9308 0.1339
-6.000 -0.3686 0.05281 0.04472 -0.1079 0.9211 0.1363
-5.750 -0.3313 0.05115 0.04267 -0.1110 0.9114 0.1378
-5.500 -0.2999 0.05012 0.04133 -0.1126 0.9020 0.1398
-5.250 -0.2595 0.04921 0.04022 -0.1150 0.8937 0.1441
-5.000 -0.2395 0.04876 0.03990 -0.1144 0.8842 0.1496
-4.750 -0.1972 0.04833 0.03929 -0.1168 0.8768 0.1580
-4.500 -0.1823 0.04814 0.03930 -0.1159 0.8686 0.1645
-4.250 -0.1426 0.04761 0.03893 -0.1190 0.8618 0.1809
-4.000 -0.1124 0.04694 0.03889 -0.1219 0.8546 0.2234
-3.750 -0.0933 0.04961 0.04244 -0.1190 0.8471 0.3838
-3.500 -0.0898 0.05374 0.04658 -0.1110 0.8412 0.4396
-3.250 -0.0931 0.05620 0.04902 -0.1049 0.8368 0.4670
-3.000 -0.0938 0.05855 0.05141 -0.0981 0.8330 0.4884
-2.750 -0.0844 0.06081 0.05361 -0.0928 0.8290 0.5188
-2.500 -0.0836 0.06286 0.05572 -0.0852 0.8258 0.5427
-2.250 -0.1763 0.06134 0.05442 -0.0860 0.9547 0.4932
-2.000 -0.1694 0.06322 0.05624 -0.0819 0.9550 0.5188
-1.750 -0.1719 0.06473 0.05782 -0.0751 0.9545 0.5402
-1.500 -0.1717 0.06573 0.05883 -0.0696 0.9530 0.5619
-1.250 -0.1627 0.06659 0.05961 -0.0664 0.9480 0.5838
-1.000 -0.1440 0.06795 0.06086 -0.0649 0.9427 0.6064
-0.750 -0.1277 0.06943 0.06226 -0.0626 0.9395 0.6273
-0.500 -0.1207 0.06934 0.06211 -0.0600 0.9330 0.6435
-0.250 -0.1005 0.07027 0.06294 -0.0595 0.9276 0.6624
0.000 -0.0653 0.07213 0.06461 -0.0631 0.9243 0.6754
0.250 -0.0554 0.07165 0.06405 -0.0626 0.9179 0.6796
0.500 -0.0181 0.07301 0.06519 -0.0675 0.9110 0.6845
0.750 0.0182 0.07476 0.06675 -0.0726 0.9072 0.6888
1.000 0.0324 0.07473 0.06664 -0.0727 0.8991 0.6918
1.250 0.0676 0.07646 0.06823 -0.0766 0.8939 0.6969
1.500 0.0885 0.07741 0.06907 -0.0785 0.8885 0.7015
1.750 0.1184 0.07865 0.07018 -0.0818 0.8799 0.7062
2.000 0.1576 0.08132 0.07274 -0.0862 0.8760 0.7118
2.250 0.1628 0.08101 0.07240 -0.0852 0.8672 0.7158
2.500 0.2028 0.08348 0.07475 -0.0901 0.8610 0.7225
2.750 0.2121 0.08398 0.07523 -0.0895 0.8534 0.7268
3.000 0.2457 0.08605 0.07721 -0.0930 0.8457 0.7335
3.250 0.2627 0.08737 0.07848 -0.0941 0.8383 0.7391
3.500 0.2957 0.08947 0.08052 -0.0970 0.8284 0.7469
3.750 0.3109 0.09050 0.08151 -0.0976 0.8160 0.7532
4.000 0.3344 0.09230 0.08329 -0.0990 0.8053 0.7600
4.250 0.3819 0.09570 0.08660 -0.1041 0.7932 0.7710
4.500 0.3860 0.09585 0.08679 -0.1025 0.7794 0.7774
4.750 0.3997 0.09740 0.08833 -0.1030 0.7677 0.7857
5.000 0.4336 0.10031 0.09124 -0.1058 0.7584 0.7969
5.250 0.4555 0.10201 0.09297 -0.1070 0.7442 0.8078
5.500 0.4636 0.10331 0.09431 -0.1065 0.7303 0.8182
5.750 0.4759 0.10509 0.09616 -0.1066 0.7169 0.8305
6.000 0.4924 0.10720 0.09835 -0.1072 0.7041 0.8461
6.250 0.5252 0.11010 0.10136 -0.1093 0.6930 0.8718
6.500 0.5313 0.11117 0.10260 -0.1082 0.6791 0.9083
6.750 0.5317 0.11276 0.10425 -0.1080 0.6667 1.0000
7.000 0.5563 0.11643 0.10785 -0.1115 0.6583 1.0000
7.250 0.5875 0.11972 0.11106 -0.1152 0.6464 1.0000
7.500 0.5883 0.12187 0.11318 -0.1156 0.6360 1.0000
7.750 0.6361 0.12667 0.11786 -0.1207 0.6289 1.0000
8.000 0.6222 0.12769 0.11887 -0.1195 0.6193 1.0000
8.250 0.6570 0.13169 0.12277 -0.1227 0.6136 1.0000
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Polar data table (+)
Polar graphs
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