MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 500,000 Max Cl/Cd: 82.74 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh80-il-500000.txt Download as CSV file: xf-mh80-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4288 0.12157 0.11983 0.0284 1.0000 0.0199
-10.750 -0.4339 0.11540 0.11366 0.0248 1.0000 0.0200
-10.000 -0.5163 0.10402 0.10208 0.0198 1.0000 0.0200
-9.750 -0.5202 0.09756 0.09565 0.0156 1.0000 0.0200
-9.500 -0.5173 0.09422 0.09234 0.0150 1.0000 0.0202
-9.250 -0.5133 0.09092 0.08907 0.0137 1.0000 0.0204
-9.000 -0.5097 0.08761 0.08579 0.0122 1.0000 0.0206
-8.750 -0.5066 0.08337 0.08136 0.0088 0.8605 0.0207
-8.500 -0.5147 0.07887 0.07669 0.0066 0.8088 0.0208
-8.250 -0.5337 0.07206 0.06978 0.0004 0.7797 0.0208
-8.000 -0.5527 0.06627 0.06384 -0.0022 0.7570 0.0208
-7.750 -0.5590 0.06127 0.05867 -0.0038 0.7374 0.0210
-7.500 -0.5602 0.05682 0.05403 -0.0046 0.7198 0.0213
-7.250 -0.5578 0.05250 0.04948 -0.0049 0.7034 0.0217
-7.000 -0.5739 0.04456 0.04044 -0.0033 0.6954 0.0239
-6.750 -0.5607 0.03971 0.03562 -0.0033 0.6796 0.0244
-6.500 -0.5425 0.03772 0.03354 -0.0029 0.6632 0.0248
-5.750 -0.4985 0.02201 0.01556 0.0040 0.6277 0.0136
-5.500 -0.4739 0.02027 0.01366 0.0046 0.6134 0.0132
-5.250 -0.4489 0.01861 0.01179 0.0054 0.5993 0.0129
-5.000 -0.4232 0.01731 0.01028 0.0061 0.5858 0.0127
-4.750 -0.3970 0.01628 0.00907 0.0068 0.5731 0.0126
-4.500 -0.3708 0.01541 0.00805 0.0074 0.5603 0.0127
-4.250 -0.3444 0.01467 0.00720 0.0080 0.5474 0.0129
-4.000 -0.3178 0.01406 0.00648 0.0086 0.5353 0.0132
-3.750 -0.2918 0.01339 0.00571 0.0092 0.5242 0.0138
-3.500 -0.2655 0.01286 0.00515 0.0097 0.5127 0.0146
-3.250 -0.2383 0.01249 0.00471 0.0101 0.5013 0.0157
-3.000 -0.2114 0.01208 0.00422 0.0105 0.4905 0.0174
-2.750 -0.1838 0.01179 0.00387 0.0109 0.4796 0.0198
-2.500 -0.1565 0.01142 0.00350 0.0112 0.4697 0.0262
-2.250 -0.1310 0.01072 0.00305 0.0118 0.4601 0.0856
-2.000 -0.1046 0.01026 0.00287 0.0120 0.4504 0.1604
-1.750 -0.0782 0.00989 0.00272 0.0123 0.4409 0.2315
-1.500 -0.0527 0.00937 0.00258 0.0127 0.4314 0.3413
-1.250 -0.0299 0.00862 0.00246 0.0135 0.4232 0.5188
-1.000 -0.0103 0.00779 0.00239 0.0153 0.4151 0.7186
-0.750 0.0109 0.00755 0.00254 0.0175 0.4075 0.8516
-0.500 0.0351 0.00764 0.00268 0.0192 0.3992 0.9050
-0.250 0.0608 0.00778 0.00273 0.0203 0.3913 0.9272
0.000 0.0880 0.00789 0.00278 0.0210 0.3832 0.9422
0.250 0.1202 0.00806 0.00284 0.0206 0.3755 0.9522
0.500 0.1536 0.00817 0.00288 0.0200 0.3679 0.9608
0.750 0.1914 0.00837 0.00294 0.0182 0.3600 0.9671
1.000 0.2298 0.00846 0.00298 0.0164 0.3525 0.9726
1.250 0.2753 0.00865 0.00302 0.0129 0.3446 0.9760
1.500 0.3198 0.00878 0.00310 0.0098 0.3377 0.9830
1.750 0.3708 0.00891 0.00311 0.0053 0.3303 0.9877
2.000 0.4148 0.00900 0.00315 0.0021 0.3238 0.9929
2.250 0.4577 0.00906 0.00313 -0.0010 0.3174 0.9966
2.500 0.4983 0.00918 0.00314 -0.0037 0.3116 1.0000
2.750 0.5236 0.00921 0.00318 -0.0032 0.3074 1.0000
3.000 0.5487 0.00928 0.00322 -0.0027 0.3027 1.0000
3.250 0.5736 0.00941 0.00328 -0.0021 0.2981 1.0000
3.500 0.5986 0.00952 0.00337 -0.0016 0.2942 1.0000
3.750 0.6235 0.00960 0.00346 -0.0011 0.2904 1.0000
4.000 0.6483 0.00972 0.00354 -0.0005 0.2865 1.0000
4.250 0.6727 0.00990 0.00366 0.0001 0.2824 1.0000
4.500 0.6972 0.01004 0.00381 0.0007 0.2788 1.0000
4.750 0.7218 0.01015 0.00393 0.0013 0.2754 1.0000
5.000 0.7462 0.01029 0.00406 0.0019 0.2720 1.0000
5.250 0.7703 0.01048 0.00422 0.0026 0.2685 1.0000
5.500 0.7941 0.01073 0.00443 0.0033 0.2648 1.0000
5.750 0.8184 0.01084 0.00459 0.0039 0.2618 1.0000
6.000 0.8426 0.01099 0.00476 0.0046 0.2586 1.0000
6.250 0.8665 0.01117 0.00494 0.0053 0.2554 1.0000
6.500 0.8899 0.01143 0.00516 0.0060 0.2522 1.0000
6.750 0.9135 0.01168 0.00542 0.0067 0.2491 1.0000
7.000 0.9377 0.01183 0.00562 0.0073 0.2461 1.0000
7.250 0.9619 0.01200 0.00583 0.0079 0.2429 1.0000
7.500 0.9858 0.01223 0.00605 0.0085 0.2400 1.0000
7.750 1.0093 0.01256 0.00634 0.0092 0.2367 1.0000
8.000 1.0333 0.01280 0.00664 0.0097 0.2338 1.0000
8.250 1.0580 0.01299 0.00688 0.0102 0.2308 1.0000
8.500 1.0825 0.01320 0.00714 0.0107 0.2278 1.0000
8.750 1.1069 0.01347 0.00740 0.0111 0.2247 1.0000
9.000 1.1304 0.01391 0.00780 0.0116 0.2210 1.0000
9.250 1.1556 0.01409 0.00809 0.0119 0.2185 1.0000
9.500 1.1807 0.01432 0.00838 0.0121 0.2153 1.0000
9.750 1.2055 0.01457 0.00868 0.0124 0.2120 1.0000
10.000 1.2294 0.01493 0.00902 0.0127 0.2087 1.0000
10.250 1.2533 0.01531 0.00945 0.0130 0.2054 1.0000
10.500 1.2780 0.01556 0.00980 0.0133 0.2023 1.0000
10.750 1.3023 0.01584 0.01014 0.0135 0.1989 1.0000
11.000 1.3256 0.01621 0.01051 0.0138 0.1954 1.0000
11.250 1.3480 0.01668 0.01102 0.0142 0.1919 1.0000
11.500 1.3718 0.01696 0.01142 0.0145 0.1887 1.0000
11.750 1.3947 0.01731 0.01183 0.0148 0.1851 1.0000
12.000 1.4158 0.01778 0.01230 0.0152 0.1814 1.0000
12.250 1.4364 0.01829 0.01288 0.0157 0.1779 1.0000
12.500 1.4580 0.01867 0.01338 0.0161 0.1743 1.0000
12.750 1.4776 0.01916 0.01391 0.0167 0.1704 1.0000
13.000 1.4931 0.01989 0.01464 0.0176 0.1665 1.0000
13.250 1.5116 0.02038 0.01527 0.0182 0.1631 1.0000
13.500 1.5264 0.02099 0.01597 0.0192 0.1591 1.0000
13.750 1.5319 0.02191 0.01691 0.0211 0.1554 1.0000
14.000 1.5380 0.02302 0.01810 0.0222 0.1518 1.0000
14.250 1.5467 0.02417 0.01936 0.0228 0.1474 1.0000
14.500 1.5494 0.02593 0.02115 0.0231 0.1431 1.0000
14.750 1.5536 0.02778 0.02308 0.0231 0.1391 1.0000
15.000 1.5576 0.02977 0.02517 0.0228 0.1344 1.0000
15.250 1.5533 0.03271 0.02812 0.0222 0.1300 1.0000
15.500 1.5538 0.03525 0.03077 0.0216 0.1260 1.0000
15.750 1.5497 0.03835 0.03396 0.0207 0.1219 1.0000
16.000 1.5381 0.04234 0.03799 0.0195 0.1183 1.0000
16.250 1.5307 0.04595 0.04170 0.0183 0.1146 1.0000
16.500 1.5203 0.04998 0.04582 0.0169 0.1111 1.0000
16.750 1.5006 0.05520 0.05109 0.0150 0.1075 1.0000
17.000 1.4874 0.05980 0.05578 0.0132 0.1047 1.0000
17.250 1.4750 0.06454 0.06061 0.0112 0.1012 1.0000
17.500 1.4565 0.07021 0.06634 0.0087 0.0979 1.0000
17.750 1.4370 0.07617 0.07234 0.0061 0.0949 1.0000
18.000 1.4254 0.08119 0.07747 0.0038 0.0917 1.0000
18.250 1.4083 0.08709 0.08343 0.0010 0.0883 1.0000
18.500 1.3891 0.09343 0.08980 -0.0021 0.0854 1.0000
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Polar data table (+)
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