MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 50,000 Max Cl/Cd: 28.73 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh62-il-50000.txt Download as CSV file: xf-mh62-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 62 9.3%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4248 0.10663 0.10085 0.0118 1.0000 0.2433
-8.750 -0.4260 0.10333 0.09760 0.0109 1.0000 0.2530
-8.500 -0.5262 0.10726 0.10114 0.0154 1.0000 0.2539
-8.250 -0.5045 0.10178 0.09567 0.0161 1.0000 0.2606
-7.750 -0.5082 0.09574 0.08980 0.0136 1.0000 0.2810
-7.500 -0.4966 0.09105 0.08515 0.0132 1.0000 0.2863
-7.250 -0.5055 0.08844 0.08267 0.0116 1.0000 0.2972
-7.000 -0.4911 0.08380 0.07806 0.0114 1.0000 0.3014
-6.750 -0.5314 0.06626 0.06041 -0.0196 1.0000 0.1365
-6.500 -0.5305 0.05749 0.05119 -0.0261 1.0000 0.1133
-6.250 -0.5231 0.05065 0.04369 -0.0289 1.0000 0.1017
-6.000 -0.5073 0.04597 0.03876 -0.0292 1.0000 0.0977
-5.750 -0.4919 0.04094 0.03305 -0.0294 1.0000 0.0929
-5.500 -0.4731 0.03702 0.02819 -0.0287 1.0000 0.0905
-5.250 -0.4522 0.03379 0.02478 -0.0279 1.0000 0.0929
-5.000 -0.4315 0.03144 0.02212 -0.0268 1.0000 0.1002
-4.750 -0.4109 0.02893 0.01936 -0.0255 1.0000 0.1078
-4.500 -0.3901 0.02670 0.01688 -0.0237 1.0000 0.1188
-4.250 -0.3719 0.02498 0.01514 -0.0218 1.0000 0.1430
-4.000 -0.3549 0.02312 0.01360 -0.0197 1.0000 0.1875
-3.750 -0.3407 0.02096 0.01223 -0.0169 1.0000 0.3024
-3.500 -0.3332 0.01987 0.01180 -0.0129 1.0000 0.4344
-3.250 -0.3240 0.01925 0.01160 -0.0088 1.0000 0.5300
-3.000 -0.3131 0.01862 0.01123 -0.0046 1.0000 0.6186
-2.750 -0.3019 0.01797 0.01094 0.0000 1.0000 0.7091
-2.500 -0.2810 0.01742 0.01075 0.0042 1.0000 0.8350
-2.250 -0.1070 0.01699 0.00919 -0.0225 1.0000 1.0000
-2.000 -0.1216 0.01687 0.00884 -0.0182 1.0000 1.0000
-1.750 -0.1191 0.01694 0.00862 -0.0156 1.0000 1.0000
-1.500 -0.1105 0.01711 0.00851 -0.0137 1.0000 1.0000
-1.250 -0.0989 0.01733 0.00847 -0.0122 1.0000 1.0000
-1.000 -0.0856 0.01760 0.00851 -0.0110 1.0000 1.0000
-0.750 -0.0712 0.01792 0.00862 -0.0099 1.0000 1.0000
-0.500 -0.0562 0.01829 0.00877 -0.0091 1.0000 1.0000
-0.250 -0.0407 0.01871 0.00901 -0.0084 1.0000 1.0000
0.000 -0.0251 0.01917 0.00933 -0.0078 1.0000 1.0000
0.250 0.0332 0.02021 0.01019 -0.0152 0.9832 1.0000
0.500 0.0890 0.02116 0.01101 -0.0219 0.9648 1.0000
0.750 0.1447 0.02206 0.01183 -0.0283 0.9457 1.0000
1.000 0.2010 0.02288 0.01262 -0.0344 0.9265 1.0000
1.250 0.2513 0.02359 0.01332 -0.0392 0.9057 1.0000
1.500 0.3102 0.02418 0.01397 -0.0451 0.8859 1.0000
1.750 0.3502 0.02475 0.01459 -0.0473 0.8641 1.0000
2.000 0.3918 0.02522 0.01512 -0.0493 0.8432 1.0000
2.250 0.4253 0.02569 0.01564 -0.0497 0.8214 1.0000
2.500 0.4543 0.02614 0.01615 -0.0492 0.7997 1.0000
2.750 0.4840 0.02644 0.01655 -0.0483 0.7787 1.0000
3.000 0.5071 0.02687 0.01704 -0.0466 0.7562 1.0000
3.250 0.5343 0.02699 0.01722 -0.0447 0.7360 1.0000
3.500 0.5553 0.02738 0.01767 -0.0426 0.7128 1.0000
3.750 0.5813 0.02726 0.01765 -0.0400 0.6933 1.0000
4.000 0.6019 0.02758 0.01806 -0.0378 0.6693 1.0000
4.250 0.6245 0.02766 0.01821 -0.0354 0.6468 1.0000
4.500 0.6486 0.02744 0.01805 -0.0325 0.6253 1.0000
4.750 0.6707 0.02755 0.01829 -0.0302 0.6005 1.0000
5.000 0.6936 0.02753 0.01833 -0.0276 0.5761 1.0000
5.250 0.7174 0.02740 0.01823 -0.0250 0.5517 1.0000
5.500 0.7415 0.02726 0.01809 -0.0224 0.5265 1.0000
5.750 0.7649 0.02737 0.01819 -0.0201 0.4993 1.0000
6.000 0.7876 0.02774 0.01866 -0.0181 0.4704 1.0000
6.250 0.8101 0.02830 0.01925 -0.0163 0.4411 1.0000
6.500 0.8323 0.02897 0.01994 -0.0145 0.4113 1.0000
6.750 0.8545 0.02978 0.02077 -0.0129 0.3822 1.0000
7.000 0.8764 0.03073 0.02173 -0.0113 0.3535 1.0000
7.250 0.8978 0.03179 0.02281 -0.0098 0.3252 1.0000
7.500 0.9187 0.03303 0.02417 -0.0084 0.2978 1.0000
7.750 0.9388 0.03443 0.02562 -0.0070 0.2713 1.0000
8.000 0.9581 0.03585 0.02707 -0.0055 0.2446 1.0000
8.250 0.9772 0.03763 0.02887 -0.0041 0.2200 1.0000
8.500 0.9952 0.03921 0.03039 -0.0027 0.1944 1.0000
8.750 1.0083 0.04202 0.03353 -0.0013 0.1746 1.0000
9.000 1.0245 0.04405 0.03548 0.0001 0.1536 1.0000
9.250 1.0356 0.04749 0.03919 0.0014 0.1401 1.0000
9.500 1.0438 0.05045 0.04236 0.0028 0.1267 1.0000
9.750 1.0408 0.05473 0.04719 0.0040 0.1204 1.0000
10.000 1.0485 0.05894 0.05149 0.0050 0.1142 1.0000
10.250 1.0325 0.06405 0.05706 0.0057 0.1133 1.0000
10.500 1.0135 0.06914 0.06244 0.0059 0.1132 1.0000
10.750 0.9923 0.07411 0.06755 0.0059 0.1139 1.0000
11.000 0.9710 0.07958 0.07310 0.0046 0.1147 1.0000
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Polar data table (+)
Polar graphs
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