MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 500,000 Max Cl/Cd: 82.83 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh60-il-500000.txt Download as CSV file: xf-mh60-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4876 0.08149 0.07977 0.0048 1.0000 0.0193
-8.750 -0.4915 0.07561 0.07392 0.0017 1.0000 0.0195
-8.500 -0.4983 0.06913 0.06747 -0.0020 1.0000 0.0197
-8.250 -0.5120 0.06235 0.06066 -0.0055 0.9352 0.0198
-8.000 -0.5636 0.05034 0.04850 -0.0148 0.9071 0.0188
-7.750 -0.5853 0.04424 0.04218 -0.0162 0.8920 0.0188
-7.500 -0.5916 0.03937 0.03710 -0.0167 0.8808 0.0191
-7.250 -0.5907 0.03494 0.03244 -0.0168 0.8716 0.0195
-7.000 -0.5847 0.03064 0.02789 -0.0168 0.8627 0.0201
-6.750 -0.5752 0.02654 0.02347 -0.0164 0.8550 0.0211
-6.500 -0.5594 0.02363 0.02020 -0.0157 0.8473 0.0229
-6.000 -0.5411 0.02267 0.01729 -0.0136 0.8486 0.0119
-5.750 -0.5196 0.01953 0.01389 -0.0126 0.8415 0.0107
-5.500 -0.4959 0.01739 0.01145 -0.0116 0.8340 0.0100
-5.250 -0.4715 0.01577 0.00959 -0.0106 0.8270 0.0096
-5.000 -0.4468 0.01453 0.00819 -0.0097 0.8197 0.0095
-4.750 -0.4216 0.01359 0.00712 -0.0090 0.8128 0.0095
-4.500 -0.3961 0.01280 0.00622 -0.0084 0.8056 0.0098
-4.250 -0.3701 0.01215 0.00546 -0.0078 0.7988 0.0103
-4.000 -0.3436 0.01160 0.00479 -0.0073 0.7916 0.0113
-3.750 -0.3173 0.01096 0.00404 -0.0068 0.7849 0.0144
-3.500 -0.2918 0.01007 0.00332 -0.0062 0.7776 0.0584
-3.250 -0.2664 0.00942 0.00299 -0.0059 0.7708 0.1350
-3.000 -0.2408 0.00884 0.00278 -0.0056 0.7634 0.2252
-2.750 -0.2143 0.00849 0.00261 -0.0054 0.7565 0.2862
-2.500 -0.1871 0.00823 0.00245 -0.0052 0.7490 0.3291
-2.250 -0.1602 0.00799 0.00232 -0.0050 0.7420 0.3789
-2.000 -0.1338 0.00766 0.00221 -0.0046 0.7344 0.4461
-1.750 -0.1072 0.00742 0.00210 -0.0043 0.7270 0.5010
-1.500 -0.0809 0.00716 0.00200 -0.0039 0.7193 0.5605
-1.250 -0.0548 0.00691 0.00193 -0.0034 0.7113 0.6223
-1.000 -0.0296 0.00664 0.00185 -0.0026 0.7036 0.6906
-0.750 -0.0048 0.00635 0.00181 -0.0017 0.6948 0.7654
-0.500 0.0199 0.00608 0.00177 -0.0005 0.6867 0.8491
-0.250 0.0599 0.00594 0.00178 -0.0025 0.6769 0.9284
0.000 0.1122 0.00597 0.00175 -0.0075 0.6663 0.9642
0.250 0.1542 0.00603 0.00173 -0.0103 0.6557 0.9835
0.500 0.1976 0.00608 0.00168 -0.0136 0.6439 0.9959
0.750 0.2333 0.00611 0.00163 -0.0152 0.6317 1.0000
1.000 0.2595 0.00613 0.00159 -0.0148 0.6192 1.0000
1.250 0.2858 0.00617 0.00157 -0.0145 0.6059 1.0000
1.500 0.3123 0.00623 0.00155 -0.0141 0.5917 1.0000
1.750 0.3388 0.00630 0.00155 -0.0138 0.5768 1.0000
2.000 0.3654 0.00638 0.00156 -0.0135 0.5610 1.0000
2.250 0.3922 0.00648 0.00159 -0.0133 0.5440 1.0000
2.500 0.4190 0.00658 0.00164 -0.0130 0.5259 1.0000
2.750 0.4457 0.00671 0.00169 -0.0128 0.5072 1.0000
3.000 0.4725 0.00686 0.00176 -0.0126 0.4883 1.0000
3.250 0.4992 0.00702 0.00185 -0.0124 0.4686 1.0000
3.500 0.5260 0.00719 0.00195 -0.0122 0.4494 1.0000
3.750 0.5527 0.00738 0.00207 -0.0120 0.4305 1.0000
4.000 0.5794 0.00756 0.00220 -0.0118 0.4116 1.0000
4.250 0.6060 0.00778 0.00235 -0.0116 0.3928 1.0000
4.500 0.6326 0.00799 0.00251 -0.0115 0.3746 1.0000
4.750 0.6591 0.00821 0.00268 -0.0113 0.3566 1.0000
5.000 0.6855 0.00845 0.00287 -0.0111 0.3379 1.0000
5.250 0.7118 0.00871 0.00308 -0.0109 0.3202 1.0000
5.500 0.7381 0.00896 0.00329 -0.0107 0.3016 1.0000
5.750 0.7642 0.00923 0.00352 -0.0105 0.2832 1.0000
6.000 0.7901 0.00954 0.00378 -0.0103 0.2647 1.0000
6.250 0.8159 0.00985 0.00406 -0.0101 0.2458 1.0000
6.500 0.8415 0.01019 0.00435 -0.0099 0.2268 1.0000
6.750 0.8667 0.01058 0.00467 -0.0097 0.2083 1.0000
7.000 0.8920 0.01094 0.00500 -0.0094 0.1910 1.0000
7.250 0.9170 0.01134 0.00537 -0.0091 0.1733 1.0000
7.500 0.9416 0.01178 0.00576 -0.0089 0.1564 1.0000
7.750 0.9658 0.01226 0.00618 -0.0085 0.1400 1.0000
8.000 0.9900 0.01272 0.00660 -0.0082 0.1250 1.0000
8.250 1.0139 0.01320 0.00706 -0.0078 0.1121 1.0000
8.500 1.0375 0.01370 0.00754 -0.0075 0.0992 1.0000
8.750 1.0606 0.01424 0.00807 -0.0070 0.0868 1.0000
9.000 1.0832 0.01481 0.00862 -0.0066 0.0747 1.0000
9.250 1.1052 0.01544 0.00922 -0.0060 0.0621 1.0000
9.500 1.1263 0.01612 0.00987 -0.0054 0.0491 1.0000
9.750 1.1463 0.01690 0.01059 -0.0047 0.0371 1.0000
10.000 1.1651 0.01775 0.01141 -0.0039 0.0282 1.0000
10.250 1.1824 0.01871 0.01236 -0.0030 0.0218 1.0000
10.500 1.2010 0.01946 0.01318 -0.0021 0.0184 1.0000
10.750 1.2157 0.02052 0.01428 -0.0009 0.0149 1.0000
11.000 1.2314 0.02138 0.01521 0.0002 0.0124 1.0000
11.250 1.2413 0.02265 0.01653 0.0019 0.0089 1.0000
11.500 1.2419 0.02420 0.01817 0.0045 0.0074 1.0000
11.750 1.2432 0.02574 0.01983 0.0067 0.0061 1.0000
12.000 1.2465 0.02736 0.02155 0.0081 0.0056 1.0000
12.250 1.2383 0.03018 0.02448 0.0094 0.0046 1.0000
12.500 1.2340 0.03290 0.02735 0.0101 0.0044 1.0000
12.750 1.2364 0.03513 0.02972 0.0103 0.0042 1.0000
13.000 1.2333 0.03809 0.03280 0.0102 0.0042 1.0000
13.250 1.2311 0.04112 0.03597 0.0099 0.0039 1.0000
13.500 1.2264 0.04458 0.03956 0.0091 0.0039 1.0000
13.750 1.2201 0.04846 0.04360 0.0080 0.0037 1.0000
14.000 1.2124 0.05266 0.04794 0.0066 0.0037 1.0000
14.250 1.2049 0.05702 0.05243 0.0050 0.0037 1.0000
14.500 1.1942 0.06197 0.05753 0.0030 0.0038 1.0000
14.750 1.1845 0.06704 0.06272 0.0008 0.0037 1.0000
15.000 1.1739 0.07249 0.06830 -0.0018 0.0035 1.0000
15.250 1.1628 0.07813 0.07406 -0.0044 0.0035 1.0000
15.500 1.1507 0.08405 0.08012 -0.0071 0.0036 1.0000
15.750 1.1393 0.09005 0.08624 -0.0100 0.0035 1.0000
16.000 1.1275 0.09625 0.09255 -0.0130 0.0035 1.0000
16.250 1.1151 0.10268 0.09911 -0.0161 0.0035 1.0000
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Polar data table (+)
Polar graphs
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