MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 100,000 Max Cl/Cd: 58.66 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh122-il-100000-n5.txt Download as CSV file: xf-mh122-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 122 9.32%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4215 0.10172 0.09706 -0.0348 1.0000 0.0211
-8.250 -0.4278 0.09935 0.09474 -0.0332 1.0000 0.0202
-8.000 -0.4337 0.09673 0.09219 -0.0325 0.9996 0.0195
-7.750 -0.4260 0.09241 0.08781 -0.0362 0.9959 0.0184
-7.500 -0.4213 0.08782 0.08325 -0.0402 0.9914 0.0174
-7.250 -0.4184 0.08336 0.07882 -0.0443 0.9858 0.0166
-7.000 -0.4120 0.07773 0.07322 -0.0507 0.9803 0.0157
-6.750 -0.4012 0.06933 0.06486 -0.0619 0.9730 0.0146
-6.500 -0.3862 0.06026 0.05550 -0.0720 0.9669 0.0132
-6.000 -0.3487 0.05125 0.04585 -0.0802 0.9586 0.0124
-5.750 -0.3328 0.04652 0.04080 -0.0831 0.9540 0.0121
-5.500 -0.3122 0.04217 0.03603 -0.0857 0.9502 0.0119
-5.250 -0.2850 0.03806 0.03143 -0.0885 0.9475 0.0117
-5.000 -0.2541 0.03442 0.02723 -0.0911 0.9457 0.0116
-4.750 -0.2257 0.03142 0.02370 -0.0924 0.9432 0.0117
-4.500 -0.2001 0.02908 0.02088 -0.0925 0.9402 0.0118
-4.250 -0.1713 0.02749 0.01889 -0.0929 0.9377 0.0126
-4.000 -0.1419 0.02532 0.01650 -0.0941 0.9359 0.0155
-3.750 -0.1108 0.02414 0.01511 -0.0949 0.9341 0.0186
-3.500 -0.0790 0.02283 0.01363 -0.0956 0.9326 0.0205
-3.250 -0.0494 0.02174 0.01229 -0.0961 0.9306 0.0237
-3.000 -0.0243 0.02098 0.01147 -0.0961 0.9271 0.0368
-2.750 0.0075 0.01934 0.01044 -0.0979 0.9251 0.1567
-2.500 0.0359 0.01824 0.01050 -0.0989 0.9232 0.4801
-2.250 0.0649 0.01825 0.01056 -0.0990 0.9208 0.5554
-2.000 0.0944 0.01831 0.01065 -0.0991 0.9188 0.6168
-1.750 0.1133 0.01843 0.01076 -0.0972 0.9142 0.6496
-1.500 0.1397 0.01848 0.01066 -0.0970 0.9108 0.6684
-1.250 0.1698 0.01850 0.01057 -0.0976 0.9082 0.6849
-1.000 0.2015 0.01852 0.01051 -0.0985 0.9061 0.7012
-0.750 0.2240 0.01862 0.01057 -0.0976 0.9016 0.7178
-0.500 0.2495 0.01870 0.01059 -0.0973 0.8976 0.7364
-0.250 0.2791 0.01872 0.01060 -0.0977 0.8948 0.7570
0.000 0.3106 0.01870 0.01059 -0.0984 0.8925 0.7807
0.250 0.3282 0.01882 0.01077 -0.0965 0.8866 0.8081
0.500 0.3535 0.01878 0.01081 -0.0959 0.8826 0.8451
0.750 0.3854 0.01863 0.01076 -0.0966 0.8800 0.9114
1.000 0.4128 0.01876 0.01086 -0.0970 0.8743 1.0000
1.250 0.4436 0.01892 0.01097 -0.0980 0.8698 1.0000
1.500 0.4793 0.01899 0.01102 -0.0998 0.8668 1.0000
1.750 0.5044 0.01923 0.01127 -0.0996 0.8606 1.0000
2.000 0.5359 0.01932 0.01136 -0.1005 0.8557 1.0000
2.250 0.5740 0.01925 0.01133 -0.1025 0.8527 1.0000
2.500 0.5958 0.01949 0.01161 -0.1016 0.8442 1.0000
2.750 0.6342 0.01930 0.01149 -0.1034 0.8402 1.0000
3.000 0.6592 0.01939 0.01173 -0.1028 0.8312 1.0000
3.250 0.7019 0.01893 0.01139 -0.1051 0.8262 1.0000
3.500 0.7300 0.01873 0.01132 -0.1047 0.8151 1.0000
3.750 0.7643 0.01819 0.01097 -0.1050 0.8023 1.0000
4.000 0.8033 0.01736 0.01029 -0.1058 0.7862 1.0000
4.250 0.8235 0.01710 0.01016 -0.1036 0.7649 1.0000
4.500 0.8474 0.01679 0.00998 -0.1021 0.7411 1.0000
4.750 0.8687 0.01659 0.00992 -0.1001 0.7104 1.0000
5.000 0.9023 0.01606 0.00943 -0.0999 0.6534 1.0000
5.250 0.9473 0.01615 0.00869 -0.1014 0.4745 1.0000
5.500 0.9544 0.01758 0.00937 -0.0976 0.3457 1.0000
5.750 0.9629 0.01905 0.01023 -0.0946 0.2411 1.0000
6.000 0.9753 0.02040 0.01115 -0.0923 0.1675 1.0000
6.250 0.9899 0.02159 0.01210 -0.0904 0.1253 1.0000
6.500 1.0052 0.02271 0.01309 -0.0885 0.0955 1.0000
6.750 1.0205 0.02384 0.01422 -0.0865 0.0776 1.0000
7.000 1.0353 0.02504 0.01541 -0.0846 0.0629 1.0000
7.250 1.0506 0.02624 0.01665 -0.0827 0.0506 1.0000
7.500 1.0649 0.02773 0.01827 -0.0805 0.0430 1.0000
7.750 1.0803 0.02915 0.01986 -0.0788 0.0343 1.0000
8.000 1.0966 0.03080 0.02164 -0.0771 0.0281 1.0000
8.250 1.1144 0.03268 0.02371 -0.0757 0.0218 1.0000
8.500 1.1320 0.03470 0.02588 -0.0743 0.0179 1.0000
8.750 1.1529 0.03791 0.02935 -0.0736 0.0152 1.0000
9.000 1.1713 0.04008 0.03192 -0.0722 0.0126 1.0000
9.250 1.1853 0.04275 0.03495 -0.0704 0.0112 1.0000
9.500 1.1945 0.04582 0.03840 -0.0681 0.0105 1.0000
9.750 1.1980 0.04891 0.04186 -0.0653 0.0101 1.0000
10.000 1.1964 0.05209 0.04539 -0.0621 0.0098 1.0000
10.250 1.1904 0.05544 0.04909 -0.0587 0.0096 1.0000
10.500 1.1808 0.05901 0.05298 -0.0556 0.0095 1.0000
10.750 1.1680 0.06283 0.05712 -0.0527 0.0094 1.0000
11.000 1.1527 0.06695 0.06154 -0.0504 0.0094 1.0000
11.250 1.1356 0.07147 0.06635 -0.0489 0.0094 1.0000
11.500 1.1168 0.07646 0.07161 -0.0483 0.0094 1.0000
11.750 1.0965 0.08213 0.07753 -0.0488 0.0095 1.0000
12.000 1.0742 0.08879 0.08443 -0.0508 0.0096 1.0000
12.250 1.0494 0.09701 0.09287 -0.0547 0.0099 1.0000
12.500 1.0224 0.10777 0.10382 -0.0616 0.0103 1.0000
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Polar data table (+)
Polar graphs
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