Rhode St. Genese 36 (rhodesg36-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Rhode St. Genese 36 (rhodesg36-il) Reynolds number: 100,000 Max Cl/Cd: 42.18 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rhodesg36-il-100000.txt Download as CSV file: xf-rhodesg36-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Rhode St. Genese 36
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0712 0.09351 0.08885 -0.0756 0.9216 0.1531
-9.500 -0.1138 0.09267 0.08806 -0.0798 0.9070 0.1582
-9.250 -0.1855 0.09278 0.08811 -0.0800 0.8872 0.1591
-9.000 -0.0713 0.08522 0.08063 -0.0805 0.8940 0.1635
-8.750 -0.0767 0.08370 0.07914 -0.0781 0.8832 0.1662
-8.500 -0.0868 0.08141 0.07685 -0.0791 0.8731 0.1712
-8.250 -0.1049 0.07719 0.07252 -0.0849 0.8638 0.1769
-7.750 -0.0691 0.07209 0.06745 -0.0829 0.8496 0.1834
-7.500 -0.1059 0.07027 0.06534 -0.0844 0.8354 0.1934
-7.250 -0.0615 0.06591 0.06112 -0.0853 0.8326 0.1969
-7.000 -0.0402 0.06344 0.05853 -0.0873 0.8270 0.2082
-6.500 -0.0345 0.05066 0.04420 -0.0918 0.8121 0.1442
-6.000 -0.0173 0.04169 0.03420 -0.0877 0.7960 0.1183
-5.750 0.0301 0.03837 0.03043 -0.0905 0.7935 0.1185
-5.500 0.0292 0.03773 0.02964 -0.0859 0.7807 0.1184
-5.250 0.0770 0.03490 0.02640 -0.0883 0.7774 0.1186
-5.000 0.1304 0.03253 0.02401 -0.0915 0.7748 0.1221
-4.750 0.1413 0.03211 0.02351 -0.0885 0.7628 0.1244
-4.500 0.1881 0.03016 0.02126 -0.0903 0.7582 0.1280
-4.250 0.2417 0.02806 0.01895 -0.0932 0.7548 0.1331
-4.000 0.2564 0.02767 0.01858 -0.0905 0.7415 0.1374
-3.750 0.3092 0.02587 0.01656 -0.0931 0.7362 0.1449
-3.500 0.3297 0.02513 0.01593 -0.0913 0.7226 0.1512
-3.250 0.3806 0.02341 0.01416 -0.0938 0.7156 0.1648
-3.000 0.4022 0.02264 0.01341 -0.0919 0.7000 0.1769
-2.750 0.4279 0.02158 0.01253 -0.0906 0.6845 0.1995
-2.500 0.4547 0.02031 0.01154 -0.0895 0.6680 0.2568
-2.250 0.4821 0.01910 0.01078 -0.0887 0.6485 0.3648
-2.000 0.6351 0.01720 0.01008 -0.1096 0.6060 1.0000
-1.750 0.6546 0.01729 0.00979 -0.1077 0.5819 1.0000
-1.500 0.6689 0.01753 0.00979 -0.1052 0.5583 1.0000
-1.250 0.6862 0.01776 0.00975 -0.1032 0.5397 1.0000
-1.000 0.7053 0.01800 0.00971 -0.1016 0.5246 1.0000
-0.750 0.7238 0.01829 0.00978 -0.0999 0.5112 1.0000
-0.500 0.7432 0.01861 0.00991 -0.0984 0.4997 1.0000
-0.250 0.7666 0.01892 0.00993 -0.0976 0.4907 1.0000
0.000 0.7856 0.01931 0.01020 -0.0961 0.4813 1.0000
0.250 0.8102 0.01967 0.01033 -0.0955 0.4739 1.0000
0.500 0.8316 0.02012 0.01067 -0.0945 0.4669 1.0000
0.750 0.8545 0.02057 0.01098 -0.0938 0.4607 1.0000
1.000 0.8821 0.02103 0.01123 -0.0939 0.4554 1.0000
1.250 0.9041 0.02158 0.01172 -0.0931 0.4506 1.0000
1.500 0.9254 0.02211 0.01222 -0.0921 0.4458 1.0000
1.750 0.9500 0.02264 0.01265 -0.0918 0.4413 1.0000
2.000 0.9790 0.02321 0.01304 -0.0922 0.4371 1.0000
2.250 1.0006 0.02387 0.01368 -0.0914 0.4333 1.0000
2.500 1.0184 0.02450 0.01437 -0.0900 0.4293 1.0000
2.750 1.0394 0.02515 0.01501 -0.0892 0.4257 1.0000
3.000 1.0633 0.02580 0.01562 -0.0889 0.4225 1.0000
3.250 1.0900 0.02650 0.01624 -0.0890 0.4196 1.0000
3.500 1.1196 0.02739 0.01702 -0.0898 0.4170 1.0000
3.750 1.1333 0.02822 0.01799 -0.0879 0.4147 1.0000
4.000 1.1475 0.02912 0.01900 -0.0861 0.4123 1.0000
4.250 1.1627 0.03003 0.02002 -0.0846 0.4095 1.0000
4.500 1.1791 0.03094 0.02100 -0.0833 0.4068 1.0000
4.750 1.1978 0.03185 0.02193 -0.0823 0.4042 1.0000
5.000 1.2191 0.03278 0.02288 -0.0819 0.4018 1.0000
5.250 1.2422 0.03382 0.02391 -0.0817 0.3999 1.0000
5.500 1.2673 0.03511 0.02518 -0.0821 0.3981 1.0000
5.750 1.2688 0.03657 0.02685 -0.0788 0.3966 1.0000
6.000 1.2643 0.03829 0.02880 -0.0748 0.3949 1.0000
6.250 1.2530 0.04036 0.03109 -0.0702 0.3933 1.0000
6.500 1.2249 0.04302 0.03396 -0.0635 0.3914 1.0000
6.750 0.5904 0.11599 0.10817 -0.0544 0.4562 1.0000
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Polar data table (+)
Polar graphs
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