MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.25 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh80-il-1000000.txt Download as CSV file: xf-mh80-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 80 12.72%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5228 0.08574 0.08356 0.0141 0.7082 0.0117
-8.750 -0.5294 0.08037 0.07816 0.0107 0.6927 0.0118
-8.500 -0.5418 0.07416 0.07193 0.0058 0.6802 0.0119
-8.250 -0.5779 0.06526 0.06299 -0.0007 0.6727 0.0117
-8.000 -0.5932 0.05792 0.05548 -0.0033 0.6628 0.0118
-7.750 -0.5998 0.05167 0.04903 -0.0042 0.6521 0.0119
-7.500 -0.6016 0.04589 0.04299 -0.0041 0.6417 0.0122
-7.250 -0.6103 0.03748 0.03372 -0.0018 0.6348 0.0135
-7.000 -0.6099 0.03127 0.02707 -0.0002 0.6250 0.0139
-6.750 -0.5899 0.02955 0.02523 0.0004 0.6106 0.0140
-6.500 -0.5693 0.02795 0.02348 0.0011 0.5968 0.0142
-6.250 -0.5606 0.01924 0.01350 0.0053 0.5899 0.0085
-6.000 -0.5363 0.01782 0.01194 0.0060 0.5763 0.0082
-5.750 -0.5121 0.01632 0.01024 0.0068 0.5635 0.0080
-5.500 -0.4868 0.01524 0.00899 0.0075 0.5514 0.0079
-5.250 -0.4611 0.01433 0.00794 0.0081 0.5393 0.0078
-4.750 -0.4086 0.01297 0.00636 0.0092 0.5158 0.0078
-4.500 -0.3820 0.01242 0.00572 0.0097 0.5051 0.0078
-4.000 -0.3280 0.01154 0.00468 0.0106 0.4827 0.0081
-3.750 -0.3005 0.01120 0.00425 0.0110 0.4724 0.0083
-3.500 -0.2731 0.01084 0.00382 0.0113 0.4622 0.0085
-3.250 -0.2459 0.01043 0.00335 0.0117 0.4531 0.0091
-3.000 -0.2180 0.01023 0.00309 0.0119 0.4430 0.0102
-2.750 -0.1900 0.00999 0.00280 0.0122 0.4337 0.0113
-2.500 -0.1618 0.00981 0.00257 0.0124 0.4240 0.0134
-2.250 -0.1340 0.00955 0.00232 0.0127 0.4152 0.0215
-2.000 -0.1066 0.00923 0.00212 0.0129 0.4069 0.0535
-1.750 -0.0793 0.00890 0.00197 0.0131 0.3986 0.1036
-1.500 -0.0519 0.00864 0.00186 0.0133 0.3905 0.1549
-1.250 -0.0245 0.00836 0.00177 0.0135 0.3821 0.2160
-1.000 0.0020 0.00798 0.00169 0.0137 0.3743 0.3126
-0.750 0.0271 0.00739 0.00160 0.0141 0.3671 0.4663
-0.500 0.0518 0.00689 0.00154 0.0147 0.3597 0.6096
-0.250 0.0729 0.00623 0.00154 0.0163 0.3540 0.7963
0.000 0.0975 0.00615 0.00163 0.0175 0.3468 0.8704
0.250 0.1246 0.00619 0.00167 0.0181 0.3403 0.8947
0.500 0.1517 0.00626 0.00171 0.0186 0.3336 0.9112
0.750 0.1788 0.00635 0.00176 0.0191 0.3272 0.9237
1.000 0.2060 0.00641 0.00180 0.0197 0.3220 0.9336
1.250 0.2329 0.00651 0.00184 0.0202 0.3160 0.9429
1.500 0.2602 0.00660 0.00189 0.0207 0.3103 0.9503
1.750 0.2869 0.00667 0.00193 0.0212 0.3053 0.9580
2.000 0.3158 0.00678 0.00199 0.0213 0.2999 0.9645
2.250 0.3447 0.00690 0.00208 0.0214 0.2950 0.9728
2.500 0.3822 0.00702 0.00216 0.0197 0.2904 0.9777
2.750 0.4186 0.00717 0.00224 0.0181 0.2849 0.9822
3.000 0.4582 0.00731 0.00234 0.0158 0.2797 0.9846
3.250 0.4989 0.00740 0.00240 0.0133 0.2758 0.9862
3.500 0.5372 0.00751 0.00246 0.0112 0.2713 0.9881
3.750 0.5729 0.00767 0.00256 0.0096 0.2659 0.9901
4.000 0.6070 0.00773 0.00262 0.0083 0.2630 0.9922
4.250 0.6397 0.00782 0.00269 0.0074 0.2597 0.9940
4.500 0.6743 0.00791 0.00276 0.0060 0.2559 0.9951
4.750 0.7079 0.00807 0.00286 0.0047 0.2512 0.9962
5.000 0.7412 0.00814 0.00294 0.0035 0.2484 0.9975
5.250 0.7743 0.00821 0.00302 0.0024 0.2455 0.9987
5.500 0.8071 0.00832 0.00311 0.0013 0.2422 0.9998
5.750 0.8331 0.00847 0.00323 0.0016 0.2389 1.0000
6.000 0.8573 0.00865 0.00340 0.0022 0.2351 1.0000
6.250 0.8819 0.00873 0.00351 0.0029 0.2330 1.0000
6.500 0.9062 0.00884 0.00363 0.0035 0.2305 1.0000
6.750 0.9303 0.00898 0.00377 0.0042 0.2277 1.0000
7.000 0.9540 0.00916 0.00394 0.0049 0.2247 1.0000
7.250 0.9773 0.00940 0.00416 0.0056 0.2208 1.0000
7.500 1.0016 0.00950 0.00430 0.0063 0.2189 1.0000
7.750 1.0257 0.00963 0.00445 0.0069 0.2165 1.0000
8.000 1.0497 0.00979 0.00462 0.0076 0.2138 1.0000
8.250 1.0737 0.00999 0.00482 0.0082 0.2105 1.0000
8.500 1.0972 0.01028 0.00509 0.0088 0.2065 1.0000
8.750 1.1223 0.01040 0.00526 0.0093 0.2046 1.0000
9.000 1.1474 0.01055 0.00544 0.0097 0.2019 1.0000
9.250 1.1724 0.01075 0.00565 0.0100 0.1987 1.0000
9.500 1.1971 0.01102 0.00591 0.0104 0.1950 1.0000
9.750 1.2222 0.01127 0.00619 0.0107 0.1918 1.0000
10.000 1.2482 0.01144 0.00640 0.0108 0.1892 1.0000
10.250 1.2738 0.01166 0.00664 0.0110 0.1857 1.0000
10.500 1.2987 0.01196 0.00694 0.0112 0.1819 1.0000
10.750 1.3236 0.01226 0.00727 0.0114 0.1785 1.0000
11.000 1.3494 0.01247 0.00752 0.0115 0.1756 1.0000
11.250 1.3745 0.01274 0.00782 0.0116 0.1719 1.0000
11.500 1.3984 0.01313 0.00820 0.0118 0.1676 1.0000
11.750 1.4232 0.01342 0.00854 0.0120 0.1645 1.0000
12.000 1.4479 0.01370 0.00887 0.0121 0.1610 1.0000
12.250 1.4712 0.01409 0.00927 0.0124 0.1569 1.0000
12.500 1.4939 0.01453 0.00973 0.0127 0.1527 1.0000
12.750 1.5176 0.01484 0.01010 0.0129 0.1489 1.0000
13.000 1.5390 0.01534 0.01060 0.0133 0.1436 1.0000
13.250 1.5603 0.01581 0.01110 0.0137 0.1383 1.0000
13.500 1.5799 0.01638 0.01167 0.0142 0.1321 1.0000
13.750 1.5985 0.01697 0.01229 0.0148 0.1265 1.0000
14.000 1.6140 0.01773 0.01303 0.0157 0.1194 1.0000
14.250 1.6288 0.01844 0.01378 0.0167 0.1144 1.0000
14.500 1.6371 0.01930 0.01466 0.0184 0.1094 1.0000
14.750 1.6352 0.02060 0.01599 0.0208 0.1033 1.0000
15.000 1.6343 0.02231 0.01772 0.0219 0.0981 1.0000
15.250 1.6332 0.02440 0.01987 0.0223 0.0934 1.0000
15.500 1.6282 0.02712 0.02262 0.0222 0.0877 1.0000
15.750 1.6201 0.03041 0.02595 0.0216 0.0823 1.0000
16.000 1.6088 0.03420 0.02980 0.0207 0.0778 1.0000
16.250 1.5957 0.03833 0.03400 0.0196 0.0746 1.0000
16.500 1.5813 0.04270 0.03845 0.0183 0.0712 1.0000
16.750 1.5647 0.04741 0.04325 0.0168 0.0692 1.0000
17.000 1.5437 0.05277 0.04869 0.0149 0.0673 1.0000
17.250 1.5256 0.05794 0.05397 0.0130 0.0664 1.0000
17.500 1.5062 0.06347 0.05959 0.0108 0.0642 1.0000
17.750 1.4833 0.06968 0.06589 0.0082 0.0617 1.0000
18.000 1.4614 0.07596 0.07225 0.0055 0.0601 1.0000
18.250 1.4397 0.08238 0.07875 0.0026 0.0584 1.0000
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