MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 100,000 Max Cl/Cd: 54.06 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh120-il-100000.txt Download as CSV file: xf-mh120-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 120 11.57%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3921 0.10891 0.10396 -0.0347 1.0000 0.1014
-9.750 -0.4063 0.10600 0.10116 -0.0381 1.0000 0.1058
-9.500 -0.4371 0.10319 0.09852 -0.0439 1.0000 0.1069
-9.250 -0.3948 0.09914 0.09437 -0.0364 1.0000 0.1151
-9.000 -0.4106 0.09619 0.09154 -0.0391 1.0000 0.1195
-8.750 -0.4087 0.09242 0.08783 -0.0381 1.0000 0.1245
-8.500 -0.4056 0.08976 0.08519 -0.0372 1.0000 0.1289
-8.250 -0.4332 0.08690 0.08252 -0.0395 1.0000 0.1335
-8.000 -0.4619 0.08432 0.08008 -0.0395 1.0000 0.1340
-7.750 -0.4445 0.08109 0.07686 -0.0361 1.0000 0.1401
-7.500 -0.4612 0.07898 0.07484 -0.0337 1.0000 0.1434
-7.250 -0.4959 0.07654 0.07250 -0.0329 1.0000 0.1473
-7.000 -0.5407 0.07479 0.07065 -0.0316 1.0000 0.1488
-6.750 -0.5126 0.07159 0.06764 -0.0271 1.0000 0.1549
-6.500 -0.5514 0.06991 0.06583 -0.0260 1.0000 0.1627
-6.250 -0.5419 0.06670 0.06276 -0.0224 1.0000 0.1671
-4.750 -0.4918 0.03757 0.03054 -0.0213 0.9841 0.0776
-4.500 -0.4593 0.03445 0.02648 -0.0210 0.9765 0.0665
-4.250 -0.4263 0.03224 0.02383 -0.0219 0.9695 0.0663
-4.000 -0.3901 0.03018 0.02137 -0.0233 0.9627 0.0659
-3.750 -0.3552 0.02799 0.01894 -0.0245 0.9563 0.0650
-3.500 -0.3171 0.02638 0.01709 -0.0260 0.9495 0.0652
-3.250 -0.2793 0.02502 0.01561 -0.0276 0.9430 0.0665
-3.000 -0.2462 0.02368 0.01439 -0.0287 0.9355 0.0708
-2.750 -0.2142 0.02300 0.01368 -0.0295 0.9275 0.0778
-2.500 -0.1817 0.02209 0.01276 -0.0303 0.9200 0.0888
-2.250 -0.1555 0.02128 0.01207 -0.0299 0.9107 0.1177
-2.000 0.0528 0.01875 0.01266 -0.0613 0.9338 0.9871
-1.750 0.1148 0.01859 0.01217 -0.0693 0.9288 1.0000
-1.500 0.1539 0.01832 0.01165 -0.0725 0.9198 1.0000
-1.250 0.1861 0.01819 0.01133 -0.0741 0.9093 1.0000
-1.000 0.2392 0.01789 0.01085 -0.0794 0.9043 1.0000
-0.750 0.2708 0.01783 0.01063 -0.0806 0.8934 1.0000
-0.500 0.3109 0.01767 0.01034 -0.0833 0.8852 1.0000
-0.250 0.3509 0.01748 0.01005 -0.0858 0.8769 1.0000
0.000 0.3791 0.01748 0.00995 -0.0861 0.8659 1.0000
0.250 0.4163 0.01733 0.00972 -0.0879 0.8576 1.0000
0.500 0.4486 0.01723 0.00956 -0.0888 0.8479 1.0000
0.750 0.4713 0.01734 0.00962 -0.0879 0.8365 1.0000
1.000 0.4981 0.01737 0.00960 -0.0876 0.8261 1.0000
1.250 0.5338 0.01721 0.00939 -0.0889 0.8181 1.0000
1.500 0.5535 0.01740 0.00956 -0.0873 0.8062 1.0000
1.750 0.5753 0.01756 0.00970 -0.0861 0.7950 1.0000
2.000 0.6019 0.01761 0.00973 -0.0856 0.7850 1.0000
2.250 0.6317 0.01756 0.00966 -0.0857 0.7756 1.0000
2.500 0.6513 0.01778 0.00990 -0.0840 0.7636 1.0000
2.750 0.6732 0.01794 0.01007 -0.0826 0.7520 1.0000
3.000 0.6976 0.01802 0.01015 -0.0816 0.7407 1.0000
3.250 0.7254 0.01801 0.01013 -0.0812 0.7300 1.0000
3.500 0.7503 0.01808 0.01025 -0.0803 0.7186 1.0000
3.750 0.7708 0.01828 0.01048 -0.0786 0.7060 1.0000
4.000 0.7923 0.01846 0.01071 -0.0771 0.6936 1.0000
4.250 0.8147 0.01862 0.01092 -0.0758 0.6812 1.0000
4.500 0.8380 0.01873 0.01109 -0.0745 0.6684 1.0000
4.750 0.8614 0.01882 0.01123 -0.0733 0.6552 1.0000
5.000 0.8845 0.01890 0.01136 -0.0719 0.6413 1.0000
5.250 0.9068 0.01898 0.01150 -0.0704 0.6266 1.0000
5.500 0.9288 0.01905 0.01166 -0.0688 0.6110 1.0000
5.750 0.9508 0.01909 0.01176 -0.0672 0.5945 1.0000
6.000 0.9733 0.01910 0.01181 -0.0656 0.5772 1.0000
6.250 0.9948 0.01913 0.01189 -0.0639 0.5588 1.0000
6.500 1.0118 0.01926 0.01211 -0.0614 0.5381 1.0000
6.750 1.0325 0.01929 0.01218 -0.0594 0.5167 1.0000
7.000 1.0473 0.01945 0.01243 -0.0565 0.4924 1.0000
7.250 1.0618 0.01964 0.01268 -0.0536 0.4660 1.0000
7.500 1.0747 0.01989 0.01294 -0.0504 0.4369 1.0000
7.750 1.0838 0.02018 0.01314 -0.0466 0.4028 1.0000
8.000 1.0888 0.02065 0.01354 -0.0422 0.3644 1.0000
8.250 1.0899 0.02129 0.01399 -0.0374 0.3218 1.0000
8.500 1.0897 0.02215 0.01467 -0.0327 0.2800 1.0000
8.750 1.0882 0.02318 0.01549 -0.0280 0.2396 1.0000
9.000 1.0851 0.02427 0.01641 -0.0231 0.2039 1.0000
9.250 1.0772 0.02574 0.01761 -0.0180 0.1542 1.0000
9.750 1.0455 0.03091 0.02193 -0.0072 0.0665 1.0000
10.000 1.0398 0.03320 0.02418 -0.0036 0.0565 1.0000
10.250 1.0359 0.03550 0.02643 -0.0007 0.0506 1.0000
10.500 1.0402 0.03744 0.02848 0.0016 0.0462 1.0000
10.750 1.0442 0.03936 0.03040 0.0034 0.0416 1.0000
11.000 1.0549 0.04166 0.03263 0.0053 0.0389 1.0000
11.250 1.0724 0.04348 0.03464 0.0067 0.0373 1.0000
11.500 1.0933 0.04568 0.03708 0.0079 0.0357 1.0000
11.750 1.1125 0.04825 0.03987 0.0090 0.0348 1.0000
12.000 1.1264 0.05118 0.04310 0.0103 0.0346 1.0000
12.250 1.1314 0.05443 0.04667 0.0119 0.0345 1.0000
12.500 1.1286 0.05796 0.05053 0.0136 0.0345 1.0000
12.750 1.1200 0.06171 0.05461 0.0152 0.0347 1.0000
13.000 1.1067 0.06576 0.05897 0.0164 0.0348 1.0000
13.250 1.0924 0.06995 0.06343 0.0170 0.0353 1.0000
13.500 1.0738 0.07472 0.06847 0.0169 0.0356 1.0000
13.750 1.0555 0.07965 0.07363 0.0162 0.0359 1.0000
14.000 1.0325 0.08552 0.07973 0.0146 0.0362 1.0000
14.250 1.0119 0.09141 0.08581 0.0123 0.0366 1.0000
14.500 0.9881 0.09820 0.09277 0.0091 0.0369 1.0000
14.750 0.9633 0.10585 0.10057 0.0050 0.0373 1.0000
15.000 0.9436 0.11327 0.10810 0.0009 0.0379 1.0000
15.250 0.9187 0.12253 0.11745 -0.0046 0.0383 1.0000
15.500 0.8977 0.13195 0.12692 -0.0098 0.0389 1.0000
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Polar data table (+)
Polar graphs
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