MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 50,000 Max Cl/Cd: 33.12 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh62-il-50000-n5.txt Download as CSV file: xf-mh62-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5483 0.09492 0.08854 -0.0001 1.0000 0.0350
-8.750 -0.5492 0.08993 0.08362 -0.0033 1.0000 0.0347
-8.500 -0.5513 0.08462 0.07839 -0.0070 1.0000 0.0343
-8.250 -0.5548 0.07885 0.07269 -0.0116 1.0000 0.0334
-8.000 -0.5616 0.07244 0.06631 -0.0170 1.0000 0.0326
-7.750 -0.5669 0.06652 0.06031 -0.0211 1.0000 0.0318
-7.500 -0.5694 0.06104 0.05466 -0.0242 1.0000 0.0317
-7.250 -0.5676 0.05598 0.04934 -0.0263 1.0000 0.0316
-7.000 -0.5613 0.05143 0.04446 -0.0276 1.0000 0.0323
-6.750 -0.5512 0.04718 0.03981 -0.0284 1.0000 0.0331
-6.500 -0.5378 0.04324 0.03539 -0.0286 1.0000 0.0341
-6.250 -0.5213 0.03958 0.03122 -0.0284 1.0000 0.0350
-6.000 -0.5020 0.03630 0.02741 -0.0279 1.0000 0.0358
-5.750 -0.4806 0.03339 0.02400 -0.0272 1.0000 0.0369
-5.500 -0.4575 0.03097 0.02110 -0.0263 1.0000 0.0384
-5.250 -0.4372 0.02883 0.01890 -0.0256 1.0000 0.0429
-5.000 -0.4151 0.02720 0.01699 -0.0246 1.0000 0.0493
-4.750 -0.3955 0.02543 0.01518 -0.0232 1.0000 0.0551
-4.500 -0.3773 0.02405 0.01375 -0.0218 1.0000 0.0681
-4.250 -0.3602 0.02266 0.01234 -0.0201 1.0000 0.0881
-4.000 -0.3429 0.02105 0.01108 -0.0188 1.0000 0.1368
-3.750 -0.3274 0.01983 0.01038 -0.0175 1.0000 0.2408
-3.500 -0.3134 0.01915 0.01007 -0.0157 1.0000 0.3347
-3.250 -0.2991 0.01865 0.00982 -0.0137 1.0000 0.4125
-3.000 -0.2659 0.01814 0.00943 -0.0148 0.9874 0.5012
-2.750 -0.2316 0.01769 0.00916 -0.0158 0.9761 0.5851
-2.500 -0.1961 0.01731 0.00896 -0.0166 0.9660 0.6757
-2.250 -0.1533 0.01701 0.00882 -0.0182 0.9577 0.7820
-2.000 -0.0850 0.01686 0.00849 -0.0247 0.9536 0.8962
-1.750 -0.0082 0.01674 0.00800 -0.0340 0.9486 0.9747
-1.500 0.0434 0.01672 0.00763 -0.0393 0.9378 1.0000
-1.250 0.0787 0.01681 0.00745 -0.0413 0.9225 1.0000
-1.000 0.1108 0.01693 0.00735 -0.0425 0.9070 1.0000
-0.750 0.1399 0.01708 0.00732 -0.0429 0.8915 1.0000
-0.500 0.1666 0.01725 0.00730 -0.0428 0.8762 1.0000
-0.250 0.1915 0.01743 0.00734 -0.0421 0.8610 1.0000
0.000 0.2151 0.01762 0.00740 -0.0411 0.8460 1.0000
0.250 0.2374 0.01783 0.00749 -0.0400 0.8304 1.0000
0.500 0.2595 0.01803 0.00760 -0.0387 0.8149 1.0000
0.750 0.2816 0.01823 0.00771 -0.0373 0.7994 1.0000
1.000 0.3039 0.01842 0.00784 -0.0360 0.7841 1.0000
1.250 0.3262 0.01860 0.00796 -0.0346 0.7686 1.0000
1.500 0.3486 0.01877 0.00810 -0.0332 0.7532 1.0000
1.750 0.3713 0.01893 0.00822 -0.0318 0.7376 1.0000
2.000 0.3940 0.01907 0.00833 -0.0304 0.7220 1.0000
2.250 0.4169 0.01923 0.00847 -0.0290 0.7053 1.0000
2.500 0.4399 0.01940 0.00865 -0.0278 0.6875 1.0000
2.750 0.4631 0.01954 0.00883 -0.0264 0.6700 1.0000
3.000 0.4866 0.01965 0.00894 -0.0251 0.6527 1.0000
3.250 0.5102 0.01982 0.00914 -0.0239 0.6332 1.0000
3.500 0.5339 0.01996 0.00930 -0.0227 0.6137 1.0000
3.750 0.5576 0.02011 0.00951 -0.0214 0.5938 1.0000
4.000 0.5814 0.02029 0.00973 -0.0202 0.5723 1.0000
4.250 0.6051 0.02049 0.00995 -0.0191 0.5504 1.0000
4.500 0.6289 0.02070 0.01017 -0.0178 0.5282 1.0000
4.750 0.6525 0.02100 0.01056 -0.0168 0.5040 1.0000
5.000 0.6760 0.02132 0.01090 -0.0157 0.4798 1.0000
5.250 0.6994 0.02169 0.01128 -0.0146 0.4554 1.0000
5.500 0.7225 0.02212 0.01172 -0.0136 0.4306 1.0000
5.750 0.7453 0.02264 0.01228 -0.0126 0.4047 1.0000
6.000 0.7678 0.02322 0.01296 -0.0117 0.3790 1.0000
6.250 0.7899 0.02385 0.01364 -0.0108 0.3535 1.0000
6.500 0.8117 0.02456 0.01438 -0.0099 0.3286 1.0000
6.750 0.8329 0.02532 0.01516 -0.0090 0.3041 1.0000
7.000 0.8536 0.02616 0.01608 -0.0081 0.2799 1.0000
7.250 0.8737 0.02709 0.01709 -0.0072 0.2559 1.0000
7.500 0.8931 0.02809 0.01822 -0.0063 0.2334 1.0000
7.750 0.9118 0.02917 0.01937 -0.0053 0.2117 1.0000
8.000 0.9294 0.03036 0.02065 -0.0044 0.1903 1.0000
8.250 0.9458 0.03163 0.02197 -0.0033 0.1704 1.0000
8.500 0.9611 0.03306 0.02351 -0.0023 0.1509 1.0000
8.750 0.9748 0.03460 0.02514 -0.0012 0.1328 1.0000
9.000 0.9867 0.03627 0.02684 -0.0001 0.1168 1.0000
9.250 0.9972 0.03812 0.02872 0.0011 0.1026 1.0000
9.500 1.0054 0.04007 0.03077 0.0023 0.0897 1.0000
9.750 1.0144 0.04236 0.03329 0.0036 0.0794 1.0000
10.000 1.0193 0.04474 0.03595 0.0048 0.0704 1.0000
10.250 1.0212 0.04693 0.03806 0.0061 0.0640 1.0000
10.500 1.0246 0.05006 0.04163 0.0074 0.0590 1.0000
10.750 1.0241 0.05278 0.04448 0.0082 0.0549 1.0000
11.000 1.0220 0.05578 0.04752 0.0086 0.0514 1.0000
11.250 1.0140 0.05982 0.05194 0.0084 0.0489 1.0000
11.500 1.0043 0.06410 0.05650 0.0074 0.0467 1.0000
11.750 0.9939 0.06878 0.06140 0.0059 0.0455 1.0000
12.000 0.9805 0.07426 0.06709 0.0036 0.0448 1.0000
12.250 0.9638 0.08068 0.07371 0.0002 0.0447 1.0000
12.500 0.9414 0.08878 0.08202 -0.0048 0.0454 1.0000
12.750 0.9121 0.09942 0.09283 -0.0115 0.0474 1.0000
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Polar data table (+)
Polar graphs
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