MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 20 9.01% (mh20-il) Reynolds number: 50,000 Max Cl/Cd: 33.72 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh20-il-50000.txt Download as CSV file: xf-mh20-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 20 9.01%
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4949 0.09582 0.09003 0.0005 1.0000 0.2500
-7.500 -0.4802 0.09141 0.08565 0.0012 1.0000 0.2624
-7.250 -0.4736 0.08760 0.08191 0.0011 1.0000 0.2749
-7.000 -0.4737 0.08439 0.07881 0.0008 1.0000 0.2889
-6.750 -0.4848 0.08205 0.07659 -0.0012 1.0000 0.3045
-5.750 -0.4613 0.05333 0.04686 -0.0300 1.0000 0.1133
-5.500 -0.4561 0.04876 0.04184 -0.0290 1.0000 0.1006
-5.250 -0.4513 0.04555 0.03852 -0.0267 1.0000 0.0966
-5.000 -0.4511 0.04245 0.03445 -0.0233 1.0000 0.0888
-4.750 -0.4431 0.03955 0.03140 -0.0209 1.0000 0.0876
-4.500 -0.4335 0.03684 0.02834 -0.0184 1.0000 0.0868
-4.250 -0.4214 0.03452 0.02543 -0.0159 1.0000 0.0884
-4.000 -0.4082 0.03249 0.02343 -0.0143 1.0000 0.0965
-3.750 -0.3910 0.03029 0.02063 -0.0122 1.0000 0.1032
-3.500 -0.3710 0.02814 0.01828 -0.0106 1.0000 0.1127
-3.250 -0.3526 0.02653 0.01650 -0.0089 1.0000 0.1425
-3.000 -0.3295 0.02441 0.01460 -0.0076 1.0000 0.1879
-2.750 -0.1604 0.01815 0.01116 -0.0268 1.0000 1.0000
-2.500 -0.1574 0.01827 0.01084 -0.0239 1.0000 1.0000
-2.250 -0.1508 0.01842 0.01059 -0.0214 1.0000 1.0000
-2.000 -0.1420 0.01861 0.01042 -0.0191 1.0000 1.0000
-1.750 -0.1318 0.01882 0.01029 -0.0170 1.0000 1.0000
-1.500 -0.1203 0.01906 0.01023 -0.0152 1.0000 1.0000
-1.250 -0.1079 0.01933 0.01022 -0.0135 1.0000 1.0000
-1.000 -0.0946 0.01963 0.01025 -0.0120 1.0000 1.0000
-0.750 -0.0806 0.01996 0.01034 -0.0106 1.0000 1.0000
-0.500 -0.0661 0.02033 0.01042 -0.0094 1.0000 1.0000
-0.250 -0.0512 0.02073 0.01062 -0.0083 1.0000 1.0000
0.000 -0.0233 0.02133 0.01103 -0.0098 0.9955 1.0000
0.250 0.0220 0.02222 0.01172 -0.0146 0.9839 1.0000
0.500 0.0659 0.02311 0.01240 -0.0191 0.9718 1.0000
0.750 0.1080 0.02398 0.01315 -0.0231 0.9592 1.0000
1.000 0.1494 0.02485 0.01394 -0.0269 0.9461 1.0000
1.250 0.1900 0.02572 0.01476 -0.0305 0.9324 1.0000
1.500 0.2302 0.02658 0.01559 -0.0338 0.9182 1.0000
1.750 0.2708 0.02743 0.01645 -0.0371 0.9036 1.0000
2.000 0.3135 0.02828 0.01733 -0.0405 0.8885 1.0000
2.250 0.3458 0.02909 0.01818 -0.0421 0.8725 1.0000
2.500 0.3772 0.02990 0.01908 -0.0434 0.8557 1.0000
2.750 0.4151 0.03067 0.01994 -0.0456 0.8388 1.0000
3.000 0.4609 0.03132 0.02073 -0.0487 0.8221 1.0000
3.250 0.4857 0.03213 0.02163 -0.0485 0.8040 1.0000
3.500 0.5150 0.03283 0.02255 -0.0486 0.7855 1.0000
3.750 0.5533 0.03327 0.02318 -0.0495 0.7683 1.0000
4.000 0.5715 0.03413 0.02415 -0.0480 0.7486 1.0000
4.250 0.6017 0.03456 0.02477 -0.0474 0.7300 1.0000
4.500 0.6285 0.03500 0.02548 -0.0463 0.7111 1.0000
4.750 0.6513 0.03551 0.02617 -0.0446 0.6909 1.0000
5.000 0.6842 0.03529 0.02619 -0.0430 0.6726 1.0000
5.250 0.7025 0.03582 0.02692 -0.0407 0.6504 1.0000
5.500 0.7292 0.03562 0.02695 -0.0383 0.6296 1.0000
5.750 0.7581 0.03495 0.02654 -0.0355 0.6081 1.0000
6.000 0.7817 0.03456 0.02640 -0.0325 0.5837 1.0000
6.250 0.8096 0.03343 0.02568 -0.0290 0.5579 1.0000
6.500 0.8408 0.03144 0.02394 -0.0249 0.5285 1.0000
6.750 0.8686 0.02932 0.02198 -0.0202 0.4897 1.0000
7.000 0.8919 0.02706 0.01960 -0.0149 0.4332 1.0000
7.250 0.9013 0.02673 0.01890 -0.0100 0.3525 1.0000
7.500 0.8970 0.02851 0.01985 -0.0052 0.2461 1.0000
7.750 0.8944 0.03159 0.02202 -0.0014 0.1660 1.0000
8.000 0.9081 0.03471 0.02468 0.0011 0.1232 1.0000
8.250 0.9320 0.03805 0.02776 0.0026 0.0989 1.0000
8.500 0.9515 0.04112 0.03102 0.0041 0.0849 1.0000
8.750 0.9719 0.04488 0.03526 0.0057 0.0790 1.0000
9.000 0.9926 0.04959 0.03993 0.0064 0.0741 1.0000
9.250 0.9958 0.05289 0.04393 0.0087 0.0722 1.0000
9.500 0.9951 0.05659 0.04817 0.0107 0.0703 1.0000
9.750 0.9922 0.06044 0.05241 0.0123 0.0697 1.0000
10.000 0.9832 0.06442 0.05674 0.0140 0.0692 1.0000
10.250 0.9696 0.06845 0.06104 0.0153 0.0694 1.0000
10.500 0.9509 0.07230 0.06508 0.0165 0.0699 1.0000
10.750 0.9316 0.07666 0.06959 0.0164 0.0707 1.0000
11.000 0.9184 0.08147 0.07450 0.0155 0.0722 1.0000
11.250 0.9011 0.08684 0.07995 0.0137 0.0729 1.0000
11.500 0.8855 0.09274 0.08590 0.0113 0.0735 1.0000
11.750 0.7067 0.10534 0.09903 0.0008 0.0965 1.0000
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Polar data table (+)
Polar graphs
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