MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 50,000 Max Cl/Cd: 32.78 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh44-il-50000-n5.txt Download as CSV file: xf-mh44-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4426 0.14593 0.13950 0.0107 1.0000 0.0972
-12.250 -0.4404 0.14284 0.13641 0.0093 1.0000 0.0969
-12.000 -0.5695 0.14298 0.13590 0.0092 1.0000 0.0501
-11.750 -0.5559 0.13866 0.13156 0.0099 1.0000 0.0489
-11.500 -0.5479 0.13456 0.12747 0.0091 1.0000 0.0475
-11.250 -0.5424 0.13046 0.12340 0.0076 1.0000 0.0460
-11.000 -0.5390 0.12615 0.11913 0.0058 1.0000 0.0451
-10.750 -0.5366 0.12163 0.11466 0.0037 1.0000 0.0435
-10.250 -0.5473 0.10910 0.10227 -0.0055 1.0000 0.0382
-10.000 -0.5437 0.10488 0.09809 -0.0069 1.0000 0.0379
-9.750 -0.5414 0.10055 0.09380 -0.0086 1.0000 0.0375
-9.500 -0.5411 0.09588 0.08919 -0.0108 1.0000 0.0372
-9.250 -0.5416 0.09108 0.08446 -0.0133 1.0000 0.0368
-9.000 -0.5444 0.08574 0.07918 -0.0166 1.0000 0.0364
-8.750 -0.5480 0.08016 0.07365 -0.0206 1.0000 0.0358
-8.500 -0.5569 0.07425 0.06778 -0.0252 1.0000 0.0353
-8.250 -0.5674 0.06939 0.06289 -0.0276 1.0000 0.0349
-8.000 -0.5754 0.06444 0.05783 -0.0295 1.0000 0.0344
-7.750 -0.5797 0.05979 0.05300 -0.0307 1.0000 0.0340
-7.500 -0.5808 0.05529 0.04823 -0.0311 1.0000 0.0338
-7.250 -0.5777 0.05110 0.04371 -0.0310 1.0000 0.0336
-7.000 -0.5715 0.04706 0.03926 -0.0304 1.0000 0.0336
-6.750 -0.5616 0.04342 0.03518 -0.0294 1.0000 0.0336
-6.500 -0.5488 0.04012 0.03143 -0.0282 1.0000 0.0340
-6.250 -0.5333 0.03717 0.02803 -0.0269 1.0000 0.0346
-6.000 -0.5158 0.03454 0.02492 -0.0254 1.0000 0.0356
-5.750 -0.4967 0.03239 0.02229 -0.0238 1.0000 0.0378
-5.500 -0.4794 0.03033 0.02016 -0.0224 1.0000 0.0409
-5.250 -0.4613 0.02870 0.01838 -0.0207 1.0000 0.0450
-5.000 -0.4426 0.02710 0.01652 -0.0187 1.0000 0.0487
-4.750 -0.4267 0.02566 0.01507 -0.0168 1.0000 0.0556
-4.500 -0.4103 0.02434 0.01364 -0.0147 1.0000 0.0658
-4.250 -0.3936 0.02300 0.01233 -0.0129 1.0000 0.0867
-4.000 -0.3756 0.02122 0.01103 -0.0117 1.0000 0.1516
-3.750 -0.3604 0.02007 0.01045 -0.0101 1.0000 0.2721
-3.500 -0.3475 0.01942 0.01021 -0.0078 1.0000 0.3717
-3.250 -0.3336 0.01890 0.00997 -0.0053 1.0000 0.4501
-3.000 -0.3177 0.01844 0.00967 -0.0031 1.0000 0.5148
-2.750 -0.3009 0.01801 0.00940 -0.0009 1.0000 0.5820
-2.500 -0.2754 0.01760 0.00918 0.0000 0.9959 0.6693
-2.250 -0.2254 0.01729 0.00911 -0.0030 0.9893 0.8011
-2.000 -0.1354 0.01730 0.00885 -0.0140 0.9898 0.9385
-1.750 -0.0665 0.01742 0.00851 -0.0226 0.9858 1.0000
-1.500 -0.0220 0.01750 0.00828 -0.0268 0.9719 1.0000
-1.250 0.0233 0.01758 0.00807 -0.0309 0.9585 1.0000
-1.000 0.0683 0.01764 0.00792 -0.0348 0.9451 1.0000
-0.750 0.1103 0.01770 0.00781 -0.0379 0.9307 1.0000
-0.500 0.1496 0.01777 0.00771 -0.0403 0.9157 1.0000
-0.250 0.1859 0.01784 0.00766 -0.0420 0.9002 1.0000
0.000 0.2154 0.01795 0.00768 -0.0423 0.8824 1.0000
0.250 0.2435 0.01807 0.00770 -0.0422 0.8648 1.0000
0.500 0.2702 0.01819 0.00774 -0.0417 0.8475 1.0000
0.750 0.2957 0.01830 0.00779 -0.0409 0.8305 1.0000
1.000 0.3183 0.01845 0.00788 -0.0396 0.8118 1.0000
1.250 0.3408 0.01859 0.00799 -0.0383 0.7933 1.0000
1.500 0.3637 0.01869 0.00806 -0.0369 0.7755 1.0000
1.750 0.3861 0.01880 0.00813 -0.0353 0.7573 1.0000
2.000 0.4080 0.01894 0.00825 -0.0338 0.7377 1.0000
2.250 0.4306 0.01903 0.00831 -0.0323 0.7192 1.0000
2.500 0.4531 0.01913 0.00843 -0.0307 0.7003 1.0000
2.750 0.4754 0.01927 0.00856 -0.0292 0.6801 1.0000
3.000 0.4983 0.01938 0.00864 -0.0276 0.6610 1.0000
3.250 0.5208 0.01956 0.00883 -0.0262 0.6396 1.0000
3.500 0.5440 0.01972 0.00901 -0.0247 0.6190 1.0000
3.750 0.5668 0.01996 0.00926 -0.0234 0.5968 1.0000
4.000 0.5899 0.02017 0.00945 -0.0220 0.5755 1.0000
4.250 0.6125 0.02047 0.00981 -0.0208 0.5520 1.0000
4.500 0.6353 0.02076 0.01011 -0.0194 0.5291 1.0000
4.750 0.6579 0.02109 0.01045 -0.0182 0.5056 1.0000
5.000 0.6802 0.02149 0.01088 -0.0169 0.4810 1.0000
5.250 0.7023 0.02190 0.01131 -0.0157 0.4564 1.0000
5.500 0.7241 0.02235 0.01180 -0.0144 0.4316 1.0000
5.750 0.7456 0.02285 0.01233 -0.0132 0.4060 1.0000
6.000 0.7665 0.02340 0.01293 -0.0119 0.3797 1.0000
6.250 0.7871 0.02401 0.01358 -0.0107 0.3535 1.0000
6.500 0.8072 0.02468 0.01432 -0.0095 0.3275 1.0000
6.750 0.8267 0.02541 0.01507 -0.0082 0.3019 1.0000
7.000 0.8457 0.02621 0.01586 -0.0069 0.2773 1.0000
7.250 0.8640 0.02711 0.01681 -0.0057 0.2526 1.0000
7.500 0.8817 0.02809 0.01785 -0.0044 0.2290 1.0000
7.750 0.8985 0.02916 0.01888 -0.0031 0.2080 1.0000
8.000 0.9148 0.03034 0.02017 -0.0018 0.1866 1.0000
8.250 0.9301 0.03160 0.02148 -0.0004 0.1684 1.0000
8.500 0.9446 0.03297 0.02293 0.0010 0.1507 1.0000
8.750 0.9589 0.03449 0.02456 0.0024 0.1354 1.0000
9.000 0.9713 0.03605 0.02622 0.0038 0.1210 1.0000
9.250 0.9837 0.03777 0.02802 0.0053 0.1093 1.0000
9.500 0.9943 0.03951 0.02980 0.0068 0.0990 1.0000
9.750 1.0032 0.04136 0.03183 0.0083 0.0893 1.0000
10.000 1.0136 0.04372 0.03444 0.0098 0.0820 1.0000
10.250 1.0210 0.04565 0.03637 0.0112 0.0756 1.0000
10.500 1.0232 0.04825 0.03939 0.0129 0.0700 1.0000
10.750 1.0244 0.05065 0.04197 0.0146 0.0656 1.0000
11.000 1.0305 0.05314 0.04441 0.0158 0.0623 1.0000
11.250 1.0220 0.05670 0.04841 0.0170 0.0601 1.0000
11.500 1.0111 0.06054 0.05258 0.0173 0.0581 1.0000
11.750 0.9987 0.06465 0.05693 0.0169 0.0563 1.0000
12.000 0.9851 0.06926 0.06175 0.0157 0.0551 1.0000
12.250 0.9693 0.07454 0.06721 0.0135 0.0543 1.0000
12.500 0.9412 0.08261 0.07552 0.0091 0.0555 1.0000
12.750 0.9068 0.09310 0.08618 0.0025 0.0577 1.0000
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Polar data table (+)
Polar graphs
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