MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 50,000 Max Cl/Cd: 33.44 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh43-il-50000.txt Download as CSV file: xf-mh43-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 43 8.5%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5244 0.11739 0.11092 0.0084 1.0000 0.2028
-9.000 -0.5071 0.11208 0.10561 0.0090 1.0000 0.2098
-8.750 -0.5275 0.11137 0.10505 0.0053 1.0000 0.2171
-8.500 -0.5014 0.10537 0.09902 0.0071 1.0000 0.2272
-8.250 -0.4988 0.10178 0.09551 0.0061 1.0000 0.2344
-8.000 -0.5161 0.10055 0.09443 0.0033 1.0000 0.2443
-7.750 -0.4998 0.09576 0.08966 0.0042 1.0000 0.2567
-7.500 -0.4910 0.09189 0.08584 0.0045 1.0000 0.2692
-7.250 -0.4931 0.08899 0.08304 0.0041 1.0000 0.2839
-7.000 -0.4990 0.08637 0.08046 0.0035 1.0000 0.2985
-6.250 -0.4916 0.06108 0.05490 -0.0286 1.0000 0.1306
-6.000 -0.4812 0.05334 0.04663 -0.0333 1.0000 0.1058
-5.750 -0.4675 0.04727 0.03987 -0.0351 1.0000 0.0945
-5.500 -0.4504 0.04307 0.03537 -0.0351 1.0000 0.0929
-5.250 -0.4325 0.03923 0.03099 -0.0348 1.0000 0.0938
-5.000 -0.4128 0.03586 0.02691 -0.0340 1.0000 0.0956
-4.750 -0.3927 0.03254 0.02336 -0.0330 1.0000 0.0991
-4.500 -0.3710 0.02976 0.02022 -0.0317 1.0000 0.1034
-4.250 -0.3508 0.02765 0.01785 -0.0303 1.0000 0.1188
-4.000 -0.3293 0.02536 0.01535 -0.0286 1.0000 0.1378
-3.750 -0.3099 0.02352 0.01360 -0.0268 1.0000 0.1775
-3.500 -0.2894 0.02131 0.01177 -0.0249 1.0000 0.2464
-3.250 -0.2749 0.01943 0.01067 -0.0224 1.0000 0.3792
-3.000 -0.2646 0.01788 0.01012 -0.0185 1.0000 0.5360
-2.750 -0.0973 0.01644 0.00877 -0.0338 1.0000 1.0000
-2.500 -0.1126 0.01615 0.00839 -0.0293 1.0000 1.0000
-2.250 -0.1208 0.01611 0.00814 -0.0251 1.0000 1.0000
-2.000 -0.1199 0.01618 0.00793 -0.0220 1.0000 1.0000
-1.750 -0.1124 0.01632 0.00777 -0.0198 1.0000 1.0000
-1.500 -0.1011 0.01650 0.00767 -0.0181 1.0000 1.0000
-1.250 -0.0877 0.01672 0.00763 -0.0168 1.0000 1.0000
-1.000 -0.0729 0.01699 0.00766 -0.0157 1.0000 1.0000
-0.750 -0.0573 0.01729 0.00770 -0.0148 1.0000 1.0000
-0.500 -0.0410 0.01764 0.00785 -0.0140 1.0000 1.0000
-0.250 -0.0243 0.01802 0.00805 -0.0134 1.0000 1.0000
0.000 -0.0075 0.01845 0.00832 -0.0129 1.0000 1.0000
0.250 0.0096 0.01891 0.00864 -0.0125 1.0000 1.0000
0.500 0.0268 0.01942 0.00902 -0.0121 1.0000 1.0000
0.750 0.0656 0.02026 0.00972 -0.0160 0.9905 1.0000
1.000 0.1148 0.02125 0.01063 -0.0216 0.9755 1.0000
1.250 0.1628 0.02220 0.01153 -0.0268 0.9600 1.0000
1.500 0.2105 0.02311 0.01242 -0.0317 0.9442 1.0000
1.750 0.2596 0.02399 0.01332 -0.0367 0.9282 1.0000
2.000 0.3003 0.02476 0.01414 -0.0399 0.9108 1.0000
2.250 0.3419 0.02550 0.01499 -0.0432 0.8929 1.0000
2.500 0.3914 0.02616 0.01577 -0.0474 0.8752 1.0000
2.750 0.4318 0.02681 0.01653 -0.0499 0.8561 1.0000
3.000 0.4725 0.02734 0.01722 -0.0520 0.8366 1.0000
3.250 0.5118 0.02780 0.01792 -0.0534 0.8170 1.0000
3.500 0.5449 0.02823 0.01851 -0.0536 0.7957 1.0000
3.750 0.5759 0.02860 0.01906 -0.0531 0.7741 1.0000
4.000 0.6106 0.02863 0.01936 -0.0523 0.7527 1.0000
4.250 0.6356 0.02888 0.01980 -0.0504 0.7284 1.0000
4.500 0.6620 0.02889 0.02000 -0.0482 0.7036 1.0000
4.750 0.6884 0.02867 0.01997 -0.0454 0.6778 1.0000
5.000 0.7140 0.02827 0.01976 -0.0423 0.6501 1.0000
5.250 0.7395 0.02764 0.01929 -0.0387 0.6203 1.0000
5.500 0.7646 0.02682 0.01869 -0.0348 0.5873 1.0000
5.750 0.7887 0.02595 0.01789 -0.0308 0.5488 1.0000
6.000 0.8097 0.02544 0.01741 -0.0271 0.5002 1.0000
6.250 0.8302 0.02501 0.01681 -0.0233 0.4427 1.0000
6.500 0.8476 0.02535 0.01679 -0.0199 0.3741 1.0000
6.750 0.8624 0.02661 0.01759 -0.0170 0.3024 1.0000
7.000 0.8777 0.02856 0.01910 -0.0147 0.2402 1.0000
7.250 0.8950 0.03096 0.02125 -0.0129 0.1923 1.0000
7.500 0.9130 0.03336 0.02338 -0.0114 0.1561 1.0000
7.750 0.9351 0.03644 0.02669 -0.0100 0.1336 1.0000
8.000 0.9546 0.03967 0.03005 -0.0088 0.1167 1.0000
8.250 0.9721 0.04300 0.03362 -0.0076 0.1041 1.0000
8.500 0.9844 0.04727 0.03864 -0.0060 0.0996 1.0000
8.750 0.9942 0.05175 0.04363 -0.0046 0.0966 1.0000
9.000 1.0049 0.05623 0.04822 -0.0037 0.0914 1.0000
9.250 0.9994 0.06071 0.05331 -0.0024 0.0896 1.0000
9.500 0.9902 0.06538 0.05842 -0.0015 0.0888 1.0000
9.750 0.9769 0.07021 0.06354 -0.0010 0.0889 1.0000
10.000 0.9613 0.07500 0.06853 -0.0010 0.0898 1.0000
10.250 0.9436 0.07970 0.07333 -0.0012 0.0906 1.0000
10.500 0.9288 0.08500 0.07869 -0.0026 0.0915 1.0000
10.750 0.9179 0.09065 0.08441 -0.0045 0.0926 1.0000
11.000 0.8803 0.10147 0.09525 -0.0123 0.1052 1.0000
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Polar data table (+)
Polar graphs
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