MH 110 10.01% (mh110-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 110 10.01% (mh110-il) Reynolds number: 50,000 Max Cl/Cd: 16.5 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh110-il-50000.txt Download as CSV file: xf-mh110-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 110 10.01%
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 -0.5837 0.09574 0.08988 0.0353 1.0000 0.3067
-7.750 -0.6070 0.06925 0.06381 0.0031 1.0000 0.1357
-7.500 -0.6833 0.06968 0.06357 0.0033 1.0000 0.1153
-7.250 -0.6900 0.06312 0.05663 0.0020 1.0000 0.1027
-7.000 -0.6967 0.05704 0.04973 0.0023 1.0000 0.0923
-6.750 -0.6847 0.05250 0.04499 0.0032 1.0000 0.0911
-6.500 -0.6731 0.04833 0.04043 0.0044 1.0000 0.0905
-6.250 -0.6595 0.04444 0.03606 0.0059 1.0000 0.0906
-6.000 -0.6427 0.04080 0.03188 0.0074 1.0000 0.0911
-5.750 -0.6224 0.03731 0.02785 0.0090 1.0000 0.0916
-5.500 -0.5990 0.03390 0.02398 0.0104 1.0000 0.0938
-5.250 -0.5740 0.03128 0.02126 0.0113 1.0000 0.1032
-5.000 -0.5475 0.02872 0.01850 0.0124 1.0000 0.1180
-4.750 -0.5204 0.02623 0.01608 0.0134 1.0000 0.1459
-4.500 -0.4961 0.02353 0.01395 0.0148 1.0000 0.2127
-4.250 -0.4804 0.02057 0.01222 0.0176 1.0000 0.3660
-4.000 -0.4724 0.01862 0.01154 0.0229 1.0000 0.5538
-3.750 -0.4523 0.01817 0.01187 0.0291 1.0000 0.7320
-3.500 -0.3735 0.02014 0.01336 0.0282 1.0000 0.8650
-3.250 -0.2326 0.02130 0.01337 0.0118 1.0000 0.9504
-3.000 -0.1260 0.01985 0.01128 -0.0044 1.0000 1.0000
-2.750 -0.1112 0.01906 0.01038 -0.0046 1.0000 1.0000
-2.500 -0.0947 0.01842 0.00962 -0.0046 1.0000 1.0000
-2.250 -0.0767 0.01791 0.00903 -0.0046 1.0000 1.0000
-2.000 -0.0572 0.01751 0.00859 -0.0047 1.0000 1.0000
-1.750 -0.0363 0.01720 0.00828 -0.0050 1.0000 1.0000
-1.500 -0.0141 0.01701 0.00815 -0.0059 1.0000 1.0000
-1.250 0.0024 0.01719 0.00844 -0.0073 1.0000 1.0000
-1.000 0.0837 0.01751 0.00857 -0.0199 0.9081 1.0000
-0.750 0.1152 0.01789 0.00860 -0.0199 0.8414 1.0000
-0.500 0.1305 0.01833 0.00876 -0.0171 0.7957 1.0000
-0.250 0.1464 0.01874 0.00894 -0.0144 0.7599 1.0000
0.000 0.1645 0.01915 0.00916 -0.0124 0.7279 1.0000
0.250 0.1835 0.01957 0.00941 -0.0105 0.6997 1.0000
0.500 0.2030 0.01998 0.00966 -0.0087 0.6753 1.0000
0.750 0.2240 0.02044 0.01002 -0.0075 0.6514 1.0000
1.000 0.2447 0.02092 0.01038 -0.0061 0.6306 1.0000
1.250 0.2663 0.02145 0.01083 -0.0051 0.6109 1.0000
1.500 0.2881 0.02199 0.01127 -0.0040 0.5937 1.0000
1.750 0.3099 0.02256 0.01177 -0.0028 0.5780 1.0000
2.000 0.3325 0.02323 0.01241 -0.0021 0.5628 1.0000
2.250 0.3550 0.02392 0.01308 -0.0014 0.5490 1.0000
2.500 0.3774 0.02463 0.01376 -0.0005 0.5361 1.0000
2.750 0.4004 0.02549 0.01472 -0.0002 0.5236 1.0000
3.000 0.4234 0.02650 0.01582 -0.0001 0.5122 1.0000
3.250 0.4460 0.02753 0.01692 0.0002 0.5018 1.0000
3.500 0.4679 0.02839 0.01778 0.0012 0.4928 1.0000
3.750 0.4902 0.02971 0.01929 0.0010 0.4832 1.0000
4.000 0.5119 0.03118 0.02091 0.0008 0.4752 1.0000
4.250 0.5333 0.03232 0.02212 0.0015 0.4676 1.0000
4.500 0.5531 0.03427 0.02430 0.0007 0.4592 1.0000
4.750 0.5739 0.03560 0.02570 0.0014 0.4533 1.0000
5.000 0.5906 0.03829 0.02865 0.0000 0.4467 1.0000
5.250 0.6091 0.03999 0.03052 0.0003 0.4402 1.0000
5.500 0.6224 0.04295 0.03368 -0.0008 0.4347 1.0000
5.750 0.6311 0.04660 0.03754 -0.0027 0.4303 1.0000
6.000 0.6523 0.04768 0.03869 -0.0008 0.4244 1.0000
6.250 0.6477 0.05301 0.04420 -0.0042 0.4216 1.0000
6.500 0.6421 0.05800 0.04927 -0.0068 0.4212 1.0000
6.750 0.6355 0.06267 0.05398 -0.0089 0.4218 1.0000
7.000 0.6307 0.06716 0.05850 -0.0107 0.4251 1.0000
7.750 0.5201 0.08583 0.07676 -0.0234 0.5637 1.0000
8.000 0.5209 0.08775 0.07871 -0.0222 0.5484 1.0000
8.250 0.5267 0.09017 0.08119 -0.0215 0.5333 1.0000
8.500 0.5320 0.09251 0.08358 -0.0208 0.5163 1.0000
8.750 0.5428 0.09524 0.08640 -0.0203 0.4990 1.0000
9.000 0.5517 0.09817 0.08941 -0.0200 0.4847 1.0000
9.250 0.5692 0.10167 0.09304 -0.0198 0.4676 1.0000
9.500 0.5860 0.10566 0.09716 -0.0196 0.4517 1.0000
9.750 0.5899 0.10857 0.10019 -0.0193 0.4375 1.0000
10.000 0.5870 0.11087 0.10251 -0.0188 0.4217 1.0000
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Polar data table (+)
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