MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 100,000 Max Cl/Cd: 50.87 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh24-il-100000.txt Download as CSV file: xf-mh24-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 24 9.01%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3979 0.08928 0.08481 -0.0319 1.0000 0.0951
-8.750 -0.4069 0.08581 0.08140 -0.0325 1.0000 0.0984
-8.500 -0.4290 0.08234 0.07802 -0.0346 1.0000 0.1006
-8.250 -0.4567 0.07884 0.07461 -0.0367 1.0000 0.1011
-8.000 -0.4828 0.07629 0.07210 -0.0353 1.0000 0.1013
-7.750 -0.5113 0.07404 0.06985 -0.0329 1.0000 0.1015
-7.500 -0.4792 0.06859 0.06450 -0.0304 1.0000 0.1065
-7.250 -0.4943 0.06586 0.06180 -0.0280 1.0000 0.1083
-7.000 -0.5116 0.06278 0.05871 -0.0262 1.0000 0.1113
-6.750 -0.5488 0.06070 0.05639 -0.0246 1.0000 0.1149
-6.500 -0.5995 0.06753 0.06265 -0.0218 1.0000 0.1149
-6.000 -0.5858 0.05992 0.05520 -0.0177 1.0000 0.1232
-5.750 -0.5870 0.05677 0.05189 -0.0156 1.0000 0.1321
-5.500 -0.5853 0.05418 0.04910 -0.0135 1.0000 0.1440
-5.250 -0.5752 0.05138 0.04624 -0.0113 1.0000 0.1514
-5.000 -0.5696 0.04893 0.04360 -0.0091 1.0000 0.1670
-4.500 -0.5216 0.03535 0.02769 -0.0031 1.0000 0.0485
-4.250 -0.5049 0.03176 0.02384 -0.0013 1.0000 0.0444
-4.000 -0.4837 0.02875 0.02014 0.0012 1.0000 0.0394
-3.750 -0.4602 0.02753 0.01844 0.0033 1.0000 0.0370
-3.500 -0.4370 0.02562 0.01622 0.0047 1.0000 0.0364
-3.250 -0.4132 0.02371 0.01409 0.0060 1.0000 0.0363
-3.000 -0.3907 0.02164 0.01201 0.0072 1.0000 0.0403
-2.750 -0.1441 0.01663 0.01033 -0.0280 1.0000 1.0000
-2.500 -0.1354 0.01646 0.00994 -0.0252 1.0000 1.0000
-2.250 -0.1261 0.01633 0.00961 -0.0224 1.0000 1.0000
-2.000 -0.1163 0.01623 0.00935 -0.0196 1.0000 1.0000
-1.750 -0.1060 0.01617 0.00913 -0.0169 1.0000 1.0000
-1.500 -0.0954 0.01614 0.00895 -0.0143 1.0000 1.0000
-1.250 -0.0847 0.01614 0.00882 -0.0116 1.0000 1.0000
-1.000 -0.0738 0.01616 0.00869 -0.0090 1.0000 1.0000
-0.750 -0.0628 0.01621 0.00863 -0.0065 1.0000 1.0000
-0.500 -0.0518 0.01629 0.00862 -0.0039 1.0000 1.0000
-0.250 -0.0406 0.01639 0.00864 -0.0015 1.0000 1.0000
0.000 -0.0292 0.01653 0.00870 0.0009 1.0000 1.0000
0.250 -0.0177 0.01670 0.00879 0.0032 1.0000 1.0000
0.500 -0.0061 0.01690 0.00894 0.0054 1.0000 1.0000
0.750 0.0058 0.01715 0.00911 0.0075 1.0000 1.0000
1.000 0.0275 0.01752 0.00945 0.0075 0.9977 1.0000
1.250 0.0827 0.01822 0.01014 0.0010 0.9860 1.0000
1.500 0.1361 0.01882 0.01076 -0.0050 0.9737 1.0000
1.750 0.1883 0.01928 0.01125 -0.0105 0.9605 1.0000
2.000 0.2397 0.01961 0.01165 -0.0157 0.9470 1.0000
2.250 0.2916 0.01979 0.01195 -0.0207 0.9332 1.0000
2.500 0.3446 0.01979 0.01207 -0.0257 0.9191 1.0000
2.750 0.3993 0.01959 0.01203 -0.0307 0.9047 1.0000
3.000 0.4581 0.01912 0.01176 -0.0360 0.8902 1.0000
3.250 0.5077 0.01849 0.01141 -0.0394 0.8722 1.0000
3.500 0.5589 0.01756 0.01072 -0.0425 0.8529 1.0000
3.750 0.5986 0.01657 0.00996 -0.0432 0.8288 1.0000
4.000 0.6383 0.01551 0.00916 -0.0435 0.7981 1.0000
4.250 0.6773 0.01464 0.00841 -0.0437 0.7501 1.0000
4.750 0.7366 0.01448 0.00784 -0.0414 0.5881 1.0000
5.000 0.7506 0.01513 0.00809 -0.0381 0.5011 1.0000
5.250 0.7608 0.01595 0.00850 -0.0344 0.4185 1.0000
5.500 0.7694 0.01689 0.00914 -0.0308 0.3399 1.0000
5.750 0.7770 0.01798 0.00981 -0.0271 0.2662 1.0000
6.000 0.7845 0.01925 0.01066 -0.0235 0.2026 1.0000
6.250 0.7923 0.02062 0.01166 -0.0201 0.1497 1.0000
6.500 0.8029 0.02215 0.01300 -0.0169 0.1149 1.0000
6.750 0.8159 0.02370 0.01442 -0.0142 0.0916 1.0000
7.000 0.8323 0.02529 0.01601 -0.0120 0.0761 1.0000
7.250 0.8555 0.02766 0.01840 -0.0109 0.0673 1.0000
7.500 0.8779 0.02985 0.02079 -0.0095 0.0606 1.0000
7.750 0.8936 0.03211 0.02333 -0.0073 0.0529 1.0000
8.000 0.9101 0.03483 0.02633 -0.0049 0.0484 1.0000
8.250 0.9178 0.03824 0.03009 -0.0019 0.0441 1.0000
8.500 0.9225 0.04043 0.03281 0.0021 0.0405 1.0000
8.750 0.9243 0.04388 0.03673 0.0061 0.0393 1.0000
9.000 0.9216 0.04759 0.04090 0.0103 0.0395 1.0000
9.250 0.9137 0.05152 0.04526 0.0146 0.0400 1.0000
9.500 0.9028 0.05542 0.04950 0.0186 0.0408 1.0000
9.750 0.8886 0.05918 0.05354 0.0225 0.0415 1.0000
10.000 0.8741 0.06252 0.05704 0.0260 0.0426 1.0000
10.250 0.8571 0.06605 0.06071 0.0289 0.0434 1.0000
10.500 0.8350 0.06978 0.06460 0.0310 0.0434 1.0000
10.750 0.8250 0.07430 0.06915 0.0315 0.0447 1.0000
11.000 0.8028 0.07886 0.07384 0.0310 0.0447 1.0000
11.250 0.7071 0.07642 0.07176 0.0314 0.0448 1.0000
11.500 0.6452 0.09329 0.08887 0.0194 0.0603 1.0000
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Polar data table (+)
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