MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.02 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh60-il-1000000-n5.txt Download as CSV file: xf-mh60-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 60 10.08%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7639 0.04953 0.04767 -0.0123 0.8492 0.0029
-9.250 -0.7958 0.04199 0.03973 -0.0134 0.8332 0.0029
-9.000 -0.8066 0.03596 0.03327 -0.0133 0.8225 0.0029
-8.750 -0.8016 0.03202 0.02894 -0.0126 0.8139 0.0029
-8.500 -0.7932 0.02818 0.02468 -0.0117 0.8056 0.0029
-8.250 -0.7795 0.02509 0.02119 -0.0108 0.7986 0.0029
-8.000 -0.7621 0.02263 0.01838 -0.0100 0.7913 0.0029
-7.750 -0.7419 0.02068 0.01613 -0.0092 0.7848 0.0029
-7.500 -0.7202 0.01903 0.01422 -0.0085 0.7779 0.0028
-7.250 -0.6973 0.01765 0.01261 -0.0079 0.7717 0.0028
-7.000 -0.6735 0.01644 0.01120 -0.0073 0.7651 0.0028
-6.750 -0.6490 0.01543 0.00999 -0.0068 0.7589 0.0028
-6.500 -0.6240 0.01451 0.00892 -0.0063 0.7524 0.0028
-6.250 -0.5987 0.01371 0.00798 -0.0059 0.7461 0.0028
-6.000 -0.5729 0.01300 0.00716 -0.0055 0.7400 0.0029
-5.750 -0.5468 0.01237 0.00641 -0.0051 0.7333 0.0029
-5.500 -0.5204 0.01182 0.00577 -0.0048 0.7272 0.0029
-5.250 -0.4937 0.01133 0.00517 -0.0045 0.7205 0.0029
-5.000 -0.4668 0.01089 0.00464 -0.0042 0.7142 0.0030
-4.750 -0.4396 0.01050 0.00419 -0.0040 0.7073 0.0030
-4.500 -0.4122 0.01017 0.00377 -0.0038 0.7006 0.0030
-4.250 -0.3846 0.00986 0.00340 -0.0036 0.6934 0.0031
-4.000 -0.3571 0.00953 0.00298 -0.0034 0.6863 0.0034
-3.750 -0.3293 0.00928 0.00268 -0.0033 0.6785 0.0039
-3.500 -0.3014 0.00907 0.00243 -0.0031 0.6711 0.0049
-3.250 -0.2736 0.00883 0.00218 -0.0030 0.6631 0.0097
-3.000 -0.2458 0.00861 0.00198 -0.0029 0.6555 0.0198
-2.750 -0.2180 0.00840 0.00179 -0.0029 0.6471 0.0333
-2.500 -0.1909 0.00803 0.00159 -0.0027 0.6387 0.0768
-2.250 -0.1640 0.00764 0.00141 -0.0026 0.6299 0.1384
-2.000 -0.1366 0.00737 0.00128 -0.0026 0.6202 0.1850
-1.750 -0.1088 0.00718 0.00118 -0.0025 0.6105 0.2237
-1.500 -0.0813 0.00697 0.00109 -0.0025 0.6003 0.2695
-1.250 -0.0533 0.00685 0.00102 -0.0024 0.5888 0.3013
-1.000 -0.0254 0.00673 0.00096 -0.0024 0.5767 0.3352
-0.750 0.0027 0.00663 0.00091 -0.0024 0.5645 0.3659
-0.500 0.0306 0.00655 0.00087 -0.0024 0.5510 0.3973
-0.250 0.0586 0.00648 0.00084 -0.0024 0.5369 0.4290
0.000 0.0866 0.00642 0.00082 -0.0024 0.5220 0.4619
0.250 0.1144 0.00637 0.00082 -0.0024 0.5064 0.4968
0.500 0.1421 0.00632 0.00082 -0.0023 0.4909 0.5342
0.750 0.1697 0.00626 0.00083 -0.0022 0.4746 0.5753
1.000 0.1970 0.00620 0.00085 -0.0021 0.4582 0.6204
1.250 0.2239 0.00614 0.00088 -0.0019 0.4417 0.6703
1.500 0.2503 0.00605 0.00092 -0.0016 0.4257 0.7272
1.750 0.2759 0.00595 0.00097 -0.0010 0.4097 0.7893
2.000 0.3006 0.00583 0.00102 -0.0002 0.3937 0.8587
2.250 0.3341 0.00579 0.00112 -0.0013 0.3765 0.9364
2.500 0.3861 0.00593 0.00121 -0.0066 0.3556 0.9706
2.750 0.4239 0.00609 0.00130 -0.0088 0.3377 0.9843
3.000 0.4566 0.00625 0.00138 -0.0099 0.3224 0.9933
3.250 0.4916 0.00642 0.00147 -0.0116 0.3055 0.9983
3.500 0.5238 0.00658 0.00158 -0.0126 0.2908 1.0000
3.750 0.5506 0.00674 0.00168 -0.0124 0.2754 1.0000
4.000 0.5773 0.00691 0.00180 -0.0122 0.2619 1.0000
4.250 0.6040 0.00709 0.00193 -0.0121 0.2478 1.0000
4.500 0.6307 0.00729 0.00207 -0.0119 0.2325 1.0000
4.750 0.6573 0.00749 0.00221 -0.0117 0.2192 1.0000
5.000 0.6838 0.00771 0.00238 -0.0115 0.2036 1.0000
5.250 0.7103 0.00793 0.00256 -0.0114 0.1908 1.0000
5.500 0.7367 0.00817 0.00274 -0.0112 0.1773 1.0000
5.750 0.7629 0.00842 0.00294 -0.0110 0.1632 1.0000
6.000 0.7890 0.00869 0.00316 -0.0108 0.1497 1.0000
6.250 0.8151 0.00896 0.00340 -0.0106 0.1374 1.0000
6.500 0.8410 0.00924 0.00364 -0.0104 0.1260 1.0000
6.750 0.8667 0.00955 0.00390 -0.0102 0.1138 1.0000
7.000 0.8922 0.00989 0.00418 -0.0100 0.1005 1.0000
7.250 0.9175 0.01024 0.00450 -0.0097 0.0883 1.0000
7.500 0.9427 0.01057 0.00480 -0.0094 0.0783 1.0000
7.750 0.9675 0.01098 0.00515 -0.0092 0.0663 1.0000
8.000 0.9917 0.01146 0.00555 -0.0088 0.0528 1.0000
8.250 1.0153 0.01200 0.00601 -0.0084 0.0390 1.0000
8.500 1.0392 0.01246 0.00644 -0.0081 0.0313 1.0000
8.750 1.0627 0.01296 0.00692 -0.0076 0.0239 1.0000
9.000 1.0857 0.01349 0.00743 -0.0072 0.0175 1.0000
9.250 1.1085 0.01404 0.00795 -0.0067 0.0126 1.0000
9.500 1.1311 0.01456 0.00848 -0.0062 0.0099 1.0000
9.750 1.1535 0.01508 0.00902 -0.0057 0.0079 1.0000
10.000 1.1758 0.01558 0.00955 -0.0051 0.0066 1.0000
10.250 1.1976 0.01611 0.01013 -0.0046 0.0054 1.0000
10.500 1.2182 0.01673 0.01077 -0.0039 0.0038 1.0000
10.750 1.2378 0.01742 0.01149 -0.0031 0.0025 1.0000
11.000 1.2565 0.01813 0.01224 -0.0022 0.0017 1.0000
11.250 1.2740 0.01891 0.01308 -0.0012 0.0011 1.0000
11.500 1.2920 0.01956 0.01380 -0.0003 0.0011 1.0000
11.750 1.3074 0.02039 0.01470 0.0009 0.0009 1.0000
12.000 1.3219 0.02119 0.01557 0.0022 0.0009 1.0000
12.250 1.3274 0.02230 0.01678 0.0045 0.0007 1.0000
12.500 1.3332 0.02340 0.01799 0.0065 0.0007 1.0000
12.750 1.3379 0.02482 0.01951 0.0080 0.0006 1.0000
13.000 1.3455 0.02618 0.02096 0.0089 0.0006 1.0000
13.250 1.3510 0.02782 0.02270 0.0097 0.0006 1.0000
13.500 1.3568 0.02954 0.02451 0.0102 0.0006 1.0000
13.750 1.3604 0.03158 0.02666 0.0106 0.0006 1.0000
14.000 1.3628 0.03386 0.02905 0.0106 0.0006 1.0000
14.250 1.3647 0.03628 0.03158 0.0105 0.0006 1.0000
14.500 1.3652 0.03897 0.03437 0.0101 0.0006 1.0000
14.750 1.3628 0.04211 0.03763 0.0094 0.0006 1.0000
15.000 1.3558 0.04600 0.04165 0.0083 0.0006 1.0000
15.250 1.3495 0.04993 0.04571 0.0070 0.0006 1.0000
15.500 1.3422 0.05418 0.05008 0.0054 0.0006 1.0000
15.750 1.3333 0.05879 0.05481 0.0035 0.0006 1.0000
16.000 1.3207 0.06419 0.06034 0.0011 0.0006 1.0000
16.250 1.3043 0.07038 0.06667 -0.0017 0.0006 1.0000
16.500 1.2872 0.07692 0.07334 -0.0048 0.0006 1.0000
16.750 1.2697 0.08363 0.08017 -0.0079 0.0006 1.0000
17.000 1.2472 0.09143 0.08811 -0.0116 0.0006 1.0000
17.250 1.2240 0.09952 0.09633 -0.0155 0.0006 1.0000
17.500 1.2043 0.10719 0.10411 -0.0191 0.0006 1.0000
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Polar data table (+)
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