MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 500,000 Max Cl/Cd: 75.05 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh62-il-500000-n5.txt Download as CSV file: xf-mh62-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5982 0.08220 0.08019 0.0054 1.0000 0.0033
-8.750 -0.6079 0.07572 0.07375 0.0012 1.0000 0.0032
-8.500 -0.6226 0.06850 0.06659 -0.0045 1.0000 0.0032
-8.250 -0.6402 0.05752 0.05556 -0.0149 1.0000 0.0031
-8.000 -0.6584 0.04510 0.04274 -0.0210 0.9537 0.0029
-7.750 -0.6923 0.03016 0.02658 -0.0194 0.9066 0.0025
-7.500 -0.6837 0.02558 0.02134 -0.0177 0.8902 0.0025
-7.250 -0.6667 0.02287 0.01816 -0.0165 0.8777 0.0025
-7.000 -0.6467 0.02080 0.01571 -0.0155 0.8668 0.0025
-6.750 -0.6249 0.01918 0.01379 -0.0147 0.8570 0.0026
-6.500 -0.6018 0.01783 0.01215 -0.0139 0.8475 0.0026
-6.250 -0.5778 0.01669 0.01079 -0.0133 0.8385 0.0027
-6.000 -0.5533 0.01570 0.00962 -0.0127 0.8301 0.0028
-5.750 -0.5283 0.01483 0.00858 -0.0122 0.8214 0.0030
-5.500 -0.5028 0.01405 0.00765 -0.0117 0.8133 0.0032
-5.250 -0.4772 0.01336 0.00683 -0.0112 0.8053 0.0035
-5.000 -0.4509 0.01277 0.00611 -0.0108 0.7971 0.0038
-4.750 -0.4245 0.01229 0.00549 -0.0104 0.7894 0.0041
-4.500 -0.3981 0.01169 0.00478 -0.0101 0.7813 0.0046
-4.250 -0.3713 0.01128 0.00428 -0.0098 0.7736 0.0052
-4.000 -0.3441 0.01099 0.00393 -0.0096 0.7655 0.0065
-3.750 -0.3169 0.01061 0.00348 -0.0094 0.7577 0.0088
-3.500 -0.2898 0.01023 0.00307 -0.0091 0.7497 0.0162
-3.250 -0.2626 0.00987 0.00273 -0.0089 0.7414 0.0349
-3.000 -0.2365 0.00932 0.00242 -0.0087 0.7334 0.0922
-2.750 -0.2102 0.00881 0.00218 -0.0085 0.7247 0.1656
-2.500 -0.1827 0.00858 0.00201 -0.0084 0.7163 0.1990
-2.250 -0.1553 0.00837 0.00186 -0.0083 0.7077 0.2339
-2.000 -0.1282 0.00808 0.00172 -0.0082 0.6985 0.2894
-1.750 -0.1010 0.00785 0.00161 -0.0081 0.6896 0.3365
-1.500 -0.0736 0.00768 0.00151 -0.0079 0.6800 0.3768
-1.250 -0.0461 0.00751 0.00142 -0.0078 0.6699 0.4155
-1.000 -0.0186 0.00737 0.00134 -0.0077 0.6595 0.4537
-0.750 0.0088 0.00723 0.00128 -0.0075 0.6485 0.4933
-0.500 0.0360 0.00710 0.00122 -0.0073 0.6369 0.5356
-0.250 0.0630 0.00695 0.00118 -0.0071 0.6245 0.5823
0.000 0.0897 0.00680 0.00115 -0.0067 0.6114 0.6333
0.250 0.1158 0.00664 0.00113 -0.0063 0.5974 0.6906
0.500 0.1412 0.00646 0.00113 -0.0056 0.5827 0.7557
0.750 0.1660 0.00627 0.00114 -0.0047 0.5671 0.8283
1.000 0.1967 0.00615 0.00117 -0.0049 0.5496 0.9081
1.500 0.2870 0.00635 0.00122 -0.0122 0.5049 0.9835
1.750 0.3232 0.00649 0.00126 -0.0141 0.4833 0.9969
2.000 0.3537 0.00663 0.00131 -0.0147 0.4614 1.0000
2.250 0.3803 0.00679 0.00137 -0.0145 0.4412 1.0000
2.500 0.4069 0.00695 0.00144 -0.0142 0.4206 1.0000
2.750 0.4335 0.00712 0.00154 -0.0140 0.4002 1.0000
3.000 0.4601 0.00730 0.00164 -0.0138 0.3801 1.0000
3.250 0.4867 0.00750 0.00175 -0.0136 0.3608 1.0000
3.500 0.5133 0.00768 0.00188 -0.0134 0.3419 1.0000
3.750 0.5398 0.00789 0.00202 -0.0132 0.3225 1.0000
4.000 0.5662 0.00811 0.00217 -0.0130 0.3046 1.0000
4.250 0.5927 0.00833 0.00234 -0.0128 0.2855 1.0000
4.500 0.6191 0.00857 0.00253 -0.0126 0.2668 1.0000
4.750 0.6454 0.00882 0.00273 -0.0124 0.2482 1.0000
5.000 0.6717 0.00909 0.00294 -0.0122 0.2295 1.0000
5.250 0.6978 0.00937 0.00317 -0.0120 0.2117 1.0000
5.500 0.7238 0.00968 0.00342 -0.0118 0.1931 1.0000
5.750 0.7497 0.00999 0.00370 -0.0116 0.1750 1.0000
6.000 0.7754 0.01034 0.00399 -0.0114 0.1577 1.0000
6.250 0.8010 0.01070 0.00431 -0.0112 0.1416 1.0000
6.500 0.8265 0.01106 0.00463 -0.0110 0.1262 1.0000
6.750 0.8518 0.01146 0.00499 -0.0107 0.1101 1.0000
7.000 0.8766 0.01191 0.00538 -0.0105 0.0932 1.0000
7.250 0.9013 0.01237 0.00582 -0.0102 0.0788 1.0000
7.500 0.9257 0.01285 0.00626 -0.0099 0.0652 1.0000
7.750 0.9500 0.01335 0.00673 -0.0095 0.0536 1.0000
8.000 0.9740 0.01387 0.00724 -0.0092 0.0433 1.0000
8.250 0.9973 0.01444 0.00780 -0.0087 0.0334 1.0000
8.500 1.0201 0.01509 0.00842 -0.0083 0.0242 1.0000
8.750 1.0423 0.01577 0.00908 -0.0078 0.0169 1.0000
9.000 1.0643 0.01646 0.00980 -0.0072 0.0119 1.0000
9.250 1.0855 0.01720 0.01055 -0.0066 0.0084 1.0000
9.500 1.1070 0.01786 0.01126 -0.0060 0.0062 1.0000
9.750 1.1275 0.01861 0.01206 -0.0054 0.0046 1.0000
10.000 1.1471 0.01940 0.01292 -0.0046 0.0033 1.0000
10.250 1.1657 0.02028 0.01388 -0.0037 0.0026 1.0000
10.500 1.1839 0.02113 0.01483 -0.0028 0.0022 1.0000
10.750 1.2005 0.02207 0.01588 -0.0018 0.0019 1.0000
11.000 1.2155 0.02309 0.01700 -0.0006 0.0016 1.0000
11.250 1.2257 0.02445 0.01852 0.0010 0.0014 1.0000
11.500 1.2358 0.02558 0.01978 0.0026 0.0013 1.0000
11.750 1.2408 0.02676 0.02109 0.0048 0.0012 1.0000
12.000 1.2437 0.02825 0.02271 0.0066 0.0011 1.0000
12.250 1.2466 0.02993 0.02452 0.0079 0.0011 1.0000
12.500 1.2491 0.03182 0.02654 0.0088 0.0011 1.0000
12.750 1.2486 0.03417 0.02904 0.0093 0.0010 1.0000
13.000 1.2469 0.03683 0.03185 0.0094 0.0010 1.0000
13.250 1.2478 0.03938 0.03453 0.0092 0.0010 1.0000
13.500 1.2419 0.04294 0.03824 0.0085 0.0008 1.0000
13.750 1.2370 0.04658 0.04203 0.0073 0.0009 1.0000
14.000 1.2290 0.05090 0.04649 0.0056 0.0008 1.0000
14.250 1.2176 0.05601 0.05177 0.0033 0.0009 1.0000
14.500 1.2080 0.06111 0.05701 0.0008 0.0008 1.0000
14.750 1.1922 0.06750 0.06357 -0.0026 0.0008 1.0000
15.000 1.1789 0.07371 0.06991 -0.0058 0.0008 1.0000
15.250 1.1619 0.08087 0.07722 -0.0096 0.0008 1.0000
15.500 1.1422 0.08875 0.08525 -0.0138 0.0009 1.0000
15.750 1.1236 0.09677 0.09340 -0.0181 0.0008 1.0000
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Polar data table (+)
Polar graphs
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