MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 50,000 Max Cl/Cd: 29.12 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh44-il-50000.txt Download as CSV file: xf-mh44-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 44 9.66%
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 -0.5037 0.09644 0.09026 0.0042 1.0000 0.2839
-7.750 -0.4781 0.09114 0.08495 0.0053 1.0000 0.2922
-7.000 -0.5557 0.06222 0.05569 -0.0287 1.0000 0.1143
-6.750 -0.5569 0.05569 0.04875 -0.0301 1.0000 0.1036
-6.500 -0.5453 0.05128 0.04413 -0.0297 1.0000 0.0986
-6.250 -0.5371 0.04660 0.03906 -0.0290 1.0000 0.0942
-6.000 -0.5299 0.04234 0.03371 -0.0272 1.0000 0.0889
-5.750 -0.5149 0.03889 0.02991 -0.0255 1.0000 0.0885
-5.500 -0.4998 0.03577 0.02650 -0.0238 1.0000 0.0902
-5.250 -0.4829 0.03346 0.02416 -0.0221 1.0000 0.0958
-5.000 -0.4651 0.03103 0.02126 -0.0200 1.0000 0.0997
-4.750 -0.4450 0.02860 0.01852 -0.0180 1.0000 0.1043
-4.500 -0.4255 0.02676 0.01660 -0.0162 1.0000 0.1177
-4.250 -0.4057 0.02494 0.01486 -0.0142 1.0000 0.1394
-4.000 -0.3873 0.02303 0.01324 -0.0120 1.0000 0.1895
-3.750 -0.3775 0.02062 0.01202 -0.0083 1.0000 0.3614
-3.500 -0.3724 0.01990 0.01184 -0.0034 1.0000 0.4782
-3.250 -0.3645 0.01937 0.01168 0.0013 1.0000 0.5707
-3.000 -0.3525 0.01869 0.01138 0.0057 1.0000 0.6597
-2.750 -0.3340 0.01796 0.01106 0.0098 1.0000 0.7717
-2.500 -0.0731 0.01785 0.00956 -0.0289 1.0000 1.0000
-2.250 -0.0973 0.01747 0.00915 -0.0233 1.0000 1.0000
-2.000 -0.1051 0.01739 0.00884 -0.0191 1.0000 1.0000
-1.750 -0.1035 0.01745 0.00866 -0.0159 1.0000 1.0000
-1.500 -0.0977 0.01759 0.00858 -0.0133 1.0000 1.0000
-1.250 -0.0898 0.01779 0.00858 -0.0110 1.0000 1.0000
-1.000 -0.0804 0.01805 0.00864 -0.0089 1.0000 1.0000
-0.750 -0.0698 0.01836 0.00878 -0.0071 1.0000 1.0000
-0.500 -0.0583 0.01872 0.00895 -0.0056 1.0000 1.0000
-0.250 -0.0460 0.01914 0.00922 -0.0042 1.0000 1.0000
0.000 -0.0334 0.01961 0.00956 -0.0031 1.0000 1.0000
0.250 -0.0204 0.02014 0.00997 -0.0021 1.0000 1.0000
0.500 0.0252 0.02107 0.01079 -0.0074 0.9874 1.0000
0.750 0.0884 0.02219 0.01180 -0.0157 0.9678 1.0000
1.000 0.1456 0.02309 0.01267 -0.0225 0.9467 1.0000
1.250 0.2048 0.02391 0.01348 -0.0293 0.9260 1.0000
1.500 0.2587 0.02457 0.01418 -0.0348 0.9040 1.0000
1.750 0.3156 0.02509 0.01478 -0.0404 0.8824 1.0000
2.000 0.3687 0.02543 0.01521 -0.0448 0.8605 1.0000
2.250 0.4082 0.02580 0.01565 -0.0465 0.8378 1.0000
2.500 0.4520 0.02591 0.01589 -0.0482 0.8166 1.0000
2.750 0.4784 0.02626 0.01631 -0.0473 0.7930 1.0000
3.000 0.5127 0.02623 0.01636 -0.0468 0.7721 1.0000
3.250 0.5360 0.02646 0.01665 -0.0449 0.7486 1.0000
3.500 0.5612 0.02653 0.01684 -0.0430 0.7263 1.0000
3.750 0.5874 0.02640 0.01678 -0.0408 0.7045 1.0000
4.000 0.6094 0.02652 0.01697 -0.0384 0.6807 1.0000
4.250 0.6351 0.02627 0.01679 -0.0357 0.6591 1.0000
4.500 0.6571 0.02635 0.01693 -0.0332 0.6341 1.0000
4.750 0.6791 0.02648 0.01712 -0.0307 0.6084 1.0000
5.000 0.7016 0.02658 0.01726 -0.0282 0.5822 1.0000
5.250 0.7242 0.02671 0.01741 -0.0257 0.5552 1.0000
5.500 0.7466 0.02693 0.01768 -0.0233 0.5271 1.0000
5.750 0.7686 0.02725 0.01801 -0.0210 0.4979 1.0000
6.000 0.7905 0.02767 0.01841 -0.0188 0.4679 1.0000
6.250 0.8123 0.02817 0.01890 -0.0167 0.4377 1.0000
6.500 0.8341 0.02873 0.01944 -0.0147 0.4073 1.0000
6.750 0.8558 0.02939 0.02000 -0.0128 0.3771 1.0000
7.000 0.8757 0.03035 0.02097 -0.0110 0.3470 1.0000
7.250 0.8952 0.03144 0.02208 -0.0092 0.3175 1.0000
7.500 0.9145 0.03263 0.02326 -0.0075 0.2893 1.0000
7.750 0.9344 0.03398 0.02454 -0.0059 0.2631 1.0000
8.000 0.9524 0.03542 0.02605 -0.0042 0.2376 1.0000
8.250 0.9677 0.03765 0.02853 -0.0026 0.2167 1.0000
8.500 0.9881 0.03919 0.02986 -0.0012 0.1948 1.0000
8.750 1.0009 0.04193 0.03292 0.0005 0.1793 1.0000
9.000 1.0122 0.04458 0.03583 0.0022 0.1646 1.0000
9.250 1.0245 0.04737 0.03877 0.0037 0.1520 1.0000
9.500 1.0234 0.05150 0.04348 0.0057 0.1457 1.0000
9.750 1.0301 0.05484 0.04698 0.0072 0.1374 1.0000
10.000 1.0175 0.05929 0.05189 0.0089 0.1339 1.0000
10.250 1.0317 0.06232 0.05487 0.0100 0.1258 1.0000
10.500 1.0138 0.06728 0.06016 0.0113 0.1256 1.0000
10.750 0.9923 0.07229 0.06539 0.0121 0.1259 1.0000
11.000 0.9705 0.07725 0.07044 0.0126 0.1264 1.0000
11.250 0.8147 0.10518 0.09806 -0.0103 0.1660 1.0000
11.500 0.8061 0.11250 0.10536 -0.0133 0.1677 1.0000
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Polar data table (+)
Polar graphs
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