MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 46 9.1% (mh46-il) Reynolds number: 200,000 Max Cl/Cd: 58.66 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh46-il-200000-n5.txt Download as CSV file: xf-mh46-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 46 9.1%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5694 0.08468 0.08134 -0.0046 1.0000 0.0076
-9.000 -0.5764 0.07879 0.07549 -0.0081 1.0000 0.0075
-8.750 -0.5853 0.07242 0.06918 -0.0124 1.0000 0.0074
-8.500 -0.5976 0.06484 0.06165 -0.0193 1.0000 0.0073
-8.250 -0.6122 0.05626 0.05294 -0.0250 1.0000 0.0071
-8.000 -0.6205 0.05008 0.04658 -0.0273 1.0000 0.0070
-7.750 -0.6252 0.04414 0.04029 -0.0281 1.0000 0.0069
-7.500 -0.6233 0.03900 0.03473 -0.0279 1.0000 0.0067
-7.250 -0.6161 0.03453 0.02975 -0.0271 1.0000 0.0066
-7.000 -0.6047 0.03064 0.02535 -0.0260 1.0000 0.0066
-6.750 -0.5892 0.02755 0.02178 -0.0247 1.0000 0.0065
-6.500 -0.5715 0.02490 0.01871 -0.0234 1.0000 0.0066
-6.250 -0.5519 0.02280 0.01625 -0.0222 1.0000 0.0067
-6.000 -0.5318 0.02100 0.01417 -0.0209 1.0000 0.0068
-5.750 -0.5120 0.01952 0.01248 -0.0195 1.0000 0.0070
-5.500 -0.4832 0.01808 0.01083 -0.0200 0.9876 0.0074
-5.250 -0.4506 0.01685 0.00941 -0.0211 0.9733 0.0079
-5.000 -0.4192 0.01560 0.00799 -0.0220 0.9596 0.0088
-4.750 -0.3879 0.01491 0.00717 -0.0229 0.9460 0.0110
-4.500 -0.3588 0.01419 0.00636 -0.0231 0.9320 0.0158
-4.250 -0.3317 0.01342 0.00550 -0.0228 0.9178 0.0257
-4.000 -0.3069 0.01268 0.00492 -0.0222 0.9038 0.0613
-3.750 -0.2832 0.01201 0.00453 -0.0215 0.8903 0.1225
-3.500 -0.2589 0.01158 0.00421 -0.0208 0.8772 0.1693
-3.250 -0.2345 0.01123 0.00391 -0.0200 0.8647 0.2147
-3.000 -0.2106 0.01085 0.00369 -0.0192 0.8525 0.2735
-2.750 -0.1865 0.01052 0.00349 -0.0183 0.8406 0.3298
-2.500 -0.1622 0.01024 0.00331 -0.0175 0.8292 0.3815
-2.250 -0.1380 0.00997 0.00315 -0.0166 0.8178 0.4350
-2.000 -0.1137 0.00972 0.00299 -0.0157 0.8060 0.4888
-1.750 -0.0895 0.00947 0.00287 -0.0148 0.7945 0.5441
-1.500 -0.0656 0.00921 0.00276 -0.0137 0.7831 0.6033
-1.250 -0.0420 0.00895 0.00267 -0.0125 0.7719 0.6679
-1.000 -0.0177 0.00867 0.00259 -0.0112 0.7609 0.7438
-0.750 0.0156 0.00843 0.00257 -0.0117 0.7495 0.8356
-0.500 0.0712 0.00838 0.00254 -0.0171 0.7372 0.9131
-0.250 0.1195 0.00840 0.00247 -0.0212 0.7244 0.9521
0.000 0.1603 0.00845 0.00242 -0.0238 0.7111 0.9757
0.500 0.2307 0.00856 0.00232 -0.0268 0.6827 1.0000
0.750 0.2554 0.00861 0.00228 -0.0262 0.6682 1.0000
1.000 0.2803 0.00868 0.00226 -0.0255 0.6532 1.0000
1.250 0.3053 0.00876 0.00225 -0.0248 0.6376 1.0000
1.500 0.3305 0.00884 0.00227 -0.0242 0.6209 1.0000
1.750 0.3556 0.00893 0.00229 -0.0236 0.6034 1.0000
2.000 0.3808 0.00904 0.00232 -0.0230 0.5854 1.0000
2.250 0.4060 0.00917 0.00237 -0.0224 0.5669 1.0000
2.500 0.4313 0.00930 0.00244 -0.0219 0.5473 1.0000
2.750 0.4564 0.00946 0.00255 -0.0213 0.5278 1.0000
3.000 0.4817 0.00962 0.00266 -0.0207 0.5073 1.0000
3.250 0.5068 0.00982 0.00278 -0.0202 0.4867 1.0000
3.500 0.5320 0.01001 0.00295 -0.0197 0.4656 1.0000
4.000 0.5820 0.01047 0.00331 -0.0186 0.4216 1.0000
4.250 0.6068 0.01073 0.00352 -0.0180 0.3984 1.0000
4.500 0.6315 0.01101 0.00375 -0.0175 0.3747 1.0000
4.750 0.6561 0.01131 0.00403 -0.0169 0.3497 1.0000
5.000 0.6804 0.01164 0.00432 -0.0163 0.3230 1.0000
5.250 0.7045 0.01201 0.00463 -0.0158 0.2956 1.0000
5.500 0.7283 0.01242 0.00497 -0.0152 0.2670 1.0000
5.750 0.7517 0.01288 0.00535 -0.0146 0.2368 1.0000
6.000 0.7749 0.01338 0.00581 -0.0140 0.2066 1.0000
6.250 0.7977 0.01393 0.00627 -0.0133 0.1771 1.0000
6.500 0.8202 0.01452 0.00678 -0.0127 0.1481 1.0000
6.750 0.8423 0.01516 0.00734 -0.0120 0.1208 1.0000
7.000 0.8639 0.01586 0.00796 -0.0113 0.0954 1.0000
7.250 0.8850 0.01662 0.00864 -0.0105 0.0724 1.0000
7.500 0.9057 0.01742 0.00939 -0.0096 0.0553 1.0000
7.750 0.9259 0.01827 0.01028 -0.0087 0.0430 1.0000
8.000 0.9459 0.01911 0.01118 -0.0077 0.0343 1.0000
8.250 0.9647 0.02009 0.01222 -0.0066 0.0285 1.0000
8.500 0.9834 0.02103 0.01329 -0.0055 0.0247 1.0000
8.750 0.9975 0.02245 0.01479 -0.0039 0.0210 1.0000
9.000 1.0163 0.02328 0.01576 -0.0028 0.0185 1.0000
9.250 1.0319 0.02443 0.01705 -0.0014 0.0165 1.0000
9.500 1.0454 0.02570 0.01841 0.0001 0.0144 1.0000
9.750 1.0568 0.02715 0.02000 0.0017 0.0125 1.0000
10.000 1.0689 0.02848 0.02150 0.0034 0.0110 1.0000
10.250 1.0787 0.02989 0.02310 0.0051 0.0100 1.0000
10.500 1.0862 0.03112 0.02442 0.0070 0.0087 1.0000
10.750 1.0823 0.03332 0.02674 0.0097 0.0080 1.0000
11.000 1.0894 0.03472 0.02834 0.0112 0.0072 1.0000
11.250 1.0903 0.03684 0.03065 0.0127 0.0068 1.0000
11.500 1.0895 0.03929 0.03330 0.0138 0.0065 1.0000
11.750 1.0875 0.04199 0.03619 0.0144 0.0061 1.0000
12.000 1.0850 0.04488 0.03926 0.0145 0.0059 1.0000
12.250 1.0793 0.04838 0.04296 0.0142 0.0057 1.0000
12.500 1.0732 0.05211 0.04688 0.0133 0.0056 1.0000
12.750 1.0661 0.05620 0.05114 0.0118 0.0055 1.0000
13.000 1.0572 0.06076 0.05585 0.0097 0.0052 1.0000
13.250 1.0464 0.06601 0.06130 0.0072 0.0053 1.0000
13.500 1.0335 0.07187 0.06734 0.0040 0.0052 1.0000
13.750 1.0159 0.07899 0.07469 0.0002 0.0054 1.0000
14.000 1.0002 0.08608 0.08194 -0.0039 0.0054 1.0000
14.250 0.9831 0.09398 0.08998 -0.0086 0.0053 1.0000
14.500 0.9587 0.10404 0.10025 -0.0143 0.0055 1.0000
14.750 0.9335 0.11500 0.11136 -0.0204 0.0058 1.0000
15.000 0.9052 0.12757 0.12406 -0.0272 0.0060 1.0000
15.250 0.8673 0.14408 0.14064 -0.0352 0.0066 1.0000
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Polar data table (+)
Polar graphs
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