MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 50,000 Max Cl/Cd: 34.25 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh26-il-50000.txt Download as CSV file: xf-mh26-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 26 10.99%
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 -0.4722 0.11179 0.10516 -0.0206 1.0000 0.2571
-9.000 -0.4945 0.11025 0.10376 -0.0201 1.0000 0.2665
-8.750 -0.5025 0.10783 0.10142 -0.0184 1.0000 0.2792
-8.250 -0.4857 0.10066 0.09431 -0.0139 1.0000 0.3111
-8.000 -0.5011 0.09894 0.09270 -0.0109 1.0000 0.3341
-7.750 -0.5100 0.09664 0.09048 -0.0085 1.0000 0.3485
-6.250 -0.4765 0.06744 0.06217 -0.0005 1.0000 0.3728
-6.000 -0.5945 0.05671 0.05104 -0.0102 1.0000 0.2077
-5.750 -0.6471 0.05910 0.05199 -0.0087 1.0000 0.1357
-5.500 -0.6415 0.05406 0.04626 -0.0059 1.0000 0.1106
-5.250 -0.6327 0.05012 0.04169 -0.0028 1.0000 0.0983
-5.000 -0.6210 0.04648 0.03771 -0.0002 1.0000 0.0930
-4.750 -0.6090 0.04378 0.03396 0.0038 1.0000 0.0874
-4.500 -0.5924 0.04090 0.03069 0.0060 1.0000 0.0877
-4.250 -0.5734 0.03808 0.02782 0.0074 1.0000 0.0913
-4.000 -0.5518 0.03571 0.02503 0.0093 1.0000 0.0926
-3.750 -0.1882 0.02741 0.01909 -0.0371 1.0000 1.0000
-3.500 -0.1833 0.02684 0.01818 -0.0344 1.0000 1.0000
-3.250 -0.1766 0.02640 0.01745 -0.0318 1.0000 1.0000
-3.000 -0.1686 0.02605 0.01681 -0.0292 1.0000 1.0000
-2.750 -0.1597 0.02578 0.01627 -0.0267 1.0000 1.0000
-2.500 -0.1500 0.02557 0.01581 -0.0241 1.0000 1.0000
-2.250 -0.1397 0.02541 0.01536 -0.0217 1.0000 1.0000
-2.000 -0.1290 0.02529 0.01504 -0.0193 1.0000 1.0000
-1.750 -0.1179 0.02522 0.01476 -0.0169 1.0000 1.0000
-1.500 -0.1066 0.02518 0.01453 -0.0145 1.0000 1.0000
-1.250 -0.0951 0.02517 0.01437 -0.0121 1.0000 1.0000
-1.000 -0.0835 0.02520 0.01424 -0.0098 1.0000 1.0000
-0.750 -0.0718 0.02526 0.01413 -0.0075 1.0000 1.0000
-0.500 -0.0600 0.02535 0.01410 -0.0053 1.0000 1.0000
-0.250 -0.0481 0.02547 0.01411 -0.0031 1.0000 1.0000
0.000 -0.0363 0.02563 0.01416 -0.0009 1.0000 1.0000
0.250 -0.0245 0.02581 0.01427 0.0013 1.0000 1.0000
0.500 -0.0127 0.02604 0.01441 0.0034 1.0000 1.0000
0.750 -0.0009 0.02629 0.01458 0.0054 1.0000 1.0000
1.000 0.0108 0.02659 0.01482 0.0074 1.0000 1.0000
1.250 0.0224 0.02692 0.01511 0.0094 1.0000 1.0000
1.500 0.0339 0.02730 0.01546 0.0113 1.0000 1.0000
1.750 0.0452 0.02772 0.01586 0.0131 1.0000 1.0000
2.000 0.0565 0.02819 0.01631 0.0148 1.0000 1.0000
2.250 0.0675 0.02871 0.01683 0.0165 1.0000 1.0000
2.500 0.0784 0.02929 0.01741 0.0181 1.0000 1.0000
2.750 0.0890 0.02992 0.01806 0.0196 1.0000 1.0000
3.000 0.0995 0.03062 0.01879 0.0209 1.0000 1.0000
3.250 0.1097 0.03139 0.01959 0.0222 1.0000 1.0000
3.500 0.1522 0.03304 0.02138 0.0168 0.9867 1.0000
3.750 0.2216 0.03512 0.02365 0.0066 0.9586 1.0000
4.000 0.2803 0.03648 0.02521 -0.0008 0.9312 1.0000
4.250 0.3341 0.03736 0.02637 -0.0067 0.9042 1.0000
4.500 0.3870 0.03785 0.02711 -0.0118 0.8772 1.0000
4.750 0.4342 0.03791 0.02744 -0.0155 0.8489 1.0000
5.000 0.4833 0.03759 0.02747 -0.0187 0.8198 1.0000
5.250 0.5401 0.03668 0.02695 -0.0223 0.7896 1.0000
5.500 0.6197 0.03429 0.02520 -0.0277 0.7581 1.0000
5.750 0.7359 0.02915 0.02091 -0.0358 0.7152 1.0000
6.000 0.8358 0.02510 0.01721 -0.0413 0.6185 1.0000
6.250 0.8632 0.02520 0.01698 -0.0383 0.5185 1.0000
6.500 0.8736 0.02625 0.01751 -0.0337 0.4338 1.0000
6.750 0.8811 0.02766 0.01839 -0.0292 0.3593 1.0000
7.000 0.8891 0.02935 0.01963 -0.0251 0.2931 1.0000
7.250 0.8999 0.03121 0.02111 -0.0218 0.2381 1.0000
7.500 0.9143 0.03323 0.02284 -0.0192 0.1945 1.0000
7.750 0.9390 0.03591 0.02540 -0.0182 0.1619 1.0000
8.250 0.9808 0.04132 0.03085 -0.0155 0.1245 1.0000
8.500 0.9896 0.04427 0.03449 -0.0115 0.1181 1.0000
8.750 1.0015 0.04726 0.03760 -0.0090 0.1096 1.0000
9.000 0.9992 0.04966 0.04048 -0.0041 0.1039 1.0000
9.250 1.0152 0.05366 0.04459 -0.0026 0.0985 1.0000
9.500 1.0097 0.05702 0.04836 0.0023 0.0978 1.0000
9.750 1.0008 0.06044 0.05219 0.0074 0.0976 1.0000
10.000 0.9894 0.06393 0.05600 0.0124 0.0976 1.0000
10.250 0.9764 0.06749 0.05982 0.0171 0.0978 1.0000
10.500 0.9634 0.07106 0.06359 0.0213 0.0981 1.0000
10.750 0.9468 0.07464 0.06735 0.0256 0.0983 1.0000
11.000 0.8685 0.07561 0.06863 0.0347 0.1045 1.0000
11.250 0.8392 0.07985 0.07297 0.0366 0.1064 1.0000
11.500 0.8143 0.08476 0.07793 0.0371 0.1082 1.0000
11.750 0.7959 0.09012 0.08332 0.0365 0.1098 1.0000
12.000 0.7906 0.09571 0.08890 0.0360 0.1112 1.0000
12.250 0.7270 0.10878 0.10188 0.0255 0.1234 1.0000
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Polar data table (+)
Polar graphs
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