MH 23 8% (mh23-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 50,000 Max Cl/Cd: 34.07 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh23-il-50000.txt Download as CSV file: xf-mh23-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 23 8%
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4826 0.09454 0.08801 -0.0107 1.0000 0.2791
-7.750 -0.4917 0.09229 0.08587 -0.0099 1.0000 0.2950
-7.500 -0.5001 0.08994 0.08363 -0.0087 1.0000 0.3092
-7.250 -0.4876 0.08627 0.08000 -0.0059 1.0000 0.3348
-7.000 -0.5068 0.08475 0.07864 -0.0036 1.0000 0.3500
-5.250 -0.5326 0.05216 0.04448 -0.0189 1.0000 0.1351
-5.000 -0.5160 0.04731 0.03950 -0.0175 1.0000 0.1181
-4.750 -0.5013 0.04348 0.03511 -0.0155 1.0000 0.1053
-4.500 -0.4849 0.04042 0.03110 -0.0129 1.0000 0.0949
-4.250 -0.4667 0.03698 0.02753 -0.0113 1.0000 0.0921
-4.000 -0.4465 0.03405 0.02416 -0.0094 1.0000 0.0884
-3.750 -0.4236 0.03133 0.02091 -0.0075 1.0000 0.0863
-3.500 -0.3990 0.02904 0.01819 -0.0059 1.0000 0.0861
-3.250 -0.1714 0.01877 0.01096 -0.0332 1.0000 1.0000
-3.000 -0.1630 0.01849 0.01022 -0.0304 1.0000 1.0000
-2.750 -0.1531 0.01829 0.00962 -0.0277 1.0000 1.0000
-2.500 -0.1421 0.01814 0.00911 -0.0250 1.0000 1.0000
-2.250 -0.1302 0.01803 0.00868 -0.0225 1.0000 1.0000
-2.000 -0.1175 0.01795 0.00831 -0.0201 1.0000 1.0000
-1.750 -0.1042 0.01790 0.00800 -0.0178 1.0000 1.0000
-1.500 -0.0905 0.01788 0.00774 -0.0156 1.0000 1.0000
-1.250 -0.0762 0.01789 0.00746 -0.0134 1.0000 1.0000
-1.000 -0.0616 0.01793 0.00729 -0.0113 1.0000 1.0000
-0.750 -0.0468 0.01799 0.00718 -0.0093 1.0000 1.0000
-0.500 -0.0317 0.01807 0.00711 -0.0073 1.0000 1.0000
-0.250 -0.0164 0.01818 0.00708 -0.0054 1.0000 1.0000
0.000 -0.0010 0.01831 0.00710 -0.0036 1.0000 1.0000
0.250 0.0144 0.01848 0.00711 -0.0018 1.0000 1.0000
0.500 0.0299 0.01867 0.00722 0.0000 1.0000 1.0000
0.750 0.0454 0.01890 0.00738 0.0016 1.0000 1.0000
1.000 0.0609 0.01916 0.00759 0.0032 1.0000 1.0000
1.250 0.0764 0.01945 0.00786 0.0047 1.0000 1.0000
1.500 0.0918 0.01979 0.00819 0.0061 1.0000 1.0000
1.750 0.1070 0.02018 0.00859 0.0074 1.0000 1.0000
2.000 0.1220 0.02061 0.00904 0.0087 1.0000 1.0000
2.250 0.1367 0.02111 0.00956 0.0098 1.0000 1.0000
2.500 0.1510 0.02167 0.01016 0.0109 1.0000 1.0000
2.750 0.1648 0.02232 0.01086 0.0118 1.0000 1.0000
3.000 0.1781 0.02304 0.01166 0.0126 1.0000 1.0000
3.250 0.1907 0.02387 0.01256 0.0132 1.0000 1.0000
3.500 0.2730 0.02591 0.01497 0.0004 0.9693 1.0000
3.750 0.3497 0.02716 0.01662 -0.0101 0.9325 1.0000
4.000 0.4270 0.02763 0.01768 -0.0192 0.8925 1.0000
4.250 0.5111 0.02690 0.01760 -0.0276 0.8483 1.0000
4.500 0.5999 0.02444 0.01592 -0.0337 0.7953 1.0000
4.750 0.6645 0.02166 0.01380 -0.0337 0.7241 1.0000
5.000 0.7018 0.02060 0.01261 -0.0300 0.6162 1.0000
5.250 0.7178 0.02137 0.01274 -0.0251 0.5011 1.0000
5.500 0.7284 0.02286 0.01352 -0.0206 0.3942 1.0000
5.750 0.7404 0.02475 0.01475 -0.0171 0.3011 1.0000
6.000 0.7565 0.02693 0.01652 -0.0145 0.2283 1.0000
6.250 0.7732 0.02902 0.01830 -0.0122 0.1773 1.0000
6.500 0.7990 0.03196 0.02130 -0.0108 0.1486 1.0000
6.750 0.8176 0.03427 0.02359 -0.0091 0.1257 1.0000
7.000 0.8385 0.03738 0.02714 -0.0074 0.1132 1.0000
7.250 0.8547 0.04092 0.03137 -0.0048 0.1081 1.0000
7.500 0.8687 0.04472 0.03564 -0.0024 0.1049 1.0000
7.750 0.8799 0.04883 0.03999 -0.0002 0.1006 1.0000
8.000 0.8785 0.05238 0.04424 0.0034 0.0971 1.0000
8.250 0.8821 0.05574 0.04789 0.0060 0.0917 1.0000
8.500 0.8739 0.06045 0.05311 0.0089 0.0940 1.0000
8.750 0.8640 0.06516 0.05816 0.0113 0.0964 1.0000
9.000 0.8553 0.06982 0.06301 0.0131 0.0986 1.0000
9.250 0.8521 0.07488 0.06815 0.0144 0.1007 1.0000
9.500 0.8134 0.07896 0.07248 0.0156 0.1055 1.0000
9.750 0.7862 0.08436 0.07791 0.0146 0.1104 1.0000
10.000 0.7759 0.09026 0.08383 0.0128 0.1165 1.0000
10.250 0.7620 0.10078 0.09432 0.0068 0.1412 1.0000
10.500 0.6957 0.12137 0.11443 -0.0197 0.2878 1.0000
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Polar data table (+)
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