MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 500,000 Max Cl/Cd: 88.1 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh42-il-500000.txt Download as CSV file: xf-mh42-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 42 8.94%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4915 0.08319 0.08106 -0.0138 1.0000 0.0155
-8.250 -0.4928 0.07825 0.07616 -0.0170 1.0000 0.0155
-8.000 -0.4961 0.07313 0.07108 -0.0210 1.0000 0.0156
-7.750 -0.5020 0.06685 0.06480 -0.0272 1.0000 0.0156
-5.500 -0.4144 0.02048 0.01563 -0.0366 0.9807 0.0093
-5.250 -0.3830 0.01722 0.01202 -0.0376 0.9695 0.0080
-5.000 -0.3534 0.01488 0.00934 -0.0377 0.9559 0.0076
-4.750 -0.3280 0.01340 0.00764 -0.0369 0.9396 0.0074
-4.500 -0.3052 0.01232 0.00638 -0.0354 0.9225 0.0075
-4.250 -0.2824 0.01147 0.00537 -0.0340 0.9063 0.0078
-4.000 -0.2587 0.01084 0.00458 -0.0329 0.8911 0.0084
-3.750 -0.2347 0.01007 0.00360 -0.0317 0.8765 0.0111
-3.500 -0.2102 0.00935 0.00294 -0.0308 0.8625 0.0415
-3.000 -0.1611 0.00830 0.00244 -0.0298 0.8356 0.1888
-2.500 -0.1092 0.00774 0.00209 -0.0290 0.8103 0.2926
-2.250 -0.0836 0.00739 0.00193 -0.0286 0.7982 0.3715
-2.000 -0.0593 0.00691 0.00182 -0.0280 0.7865 0.4899
-1.750 -0.0349 0.00654 0.00174 -0.0273 0.7751 0.5934
-1.500 -0.0108 0.00623 0.00168 -0.0263 0.7638 0.6843
-1.250 0.0133 0.00599 0.00165 -0.0252 0.7524 0.7643
-1.000 0.0376 0.00582 0.00163 -0.0241 0.7413 0.8294
-0.750 0.0630 0.00572 0.00162 -0.0231 0.7306 0.8848
-0.500 0.0944 0.00571 0.00160 -0.0234 0.7200 0.9295
-0.250 0.1345 0.00575 0.00156 -0.0258 0.7089 0.9581
0.000 0.1761 0.00579 0.00153 -0.0286 0.6973 0.9754
0.250 0.2172 0.00585 0.00151 -0.0314 0.6855 0.9875
0.500 0.2599 0.00589 0.00147 -0.0346 0.6736 0.9977
0.750 0.2903 0.00593 0.00144 -0.0352 0.6620 1.0000
1.000 0.3151 0.00599 0.00142 -0.0346 0.6504 1.0000
1.250 0.3401 0.00605 0.00142 -0.0340 0.6387 1.0000
1.500 0.3653 0.00612 0.00144 -0.0334 0.6265 1.0000
1.750 0.3908 0.00619 0.00145 -0.0329 0.6137 1.0000
2.000 0.4164 0.00627 0.00148 -0.0324 0.6007 1.0000
2.250 0.4421 0.00635 0.00152 -0.0319 0.5870 1.0000
2.500 0.4678 0.00645 0.00157 -0.0315 0.5727 1.0000
2.750 0.4936 0.00656 0.00165 -0.0310 0.5578 1.0000
3.000 0.5195 0.00666 0.00172 -0.0306 0.5418 1.0000
3.250 0.5454 0.00678 0.00181 -0.0302 0.5247 1.0000
3.500 0.5712 0.00692 0.00190 -0.0298 0.5067 1.0000
3.750 0.5970 0.00708 0.00203 -0.0294 0.4873 1.0000
4.000 0.6228 0.00725 0.00215 -0.0290 0.4657 1.0000
4.250 0.6486 0.00745 0.00229 -0.0286 0.4425 1.0000
4.500 0.6741 0.00768 0.00245 -0.0282 0.4167 1.0000
4.750 0.6995 0.00794 0.00266 -0.0278 0.3883 1.0000
5.000 0.7248 0.00823 0.00287 -0.0274 0.3589 1.0000
5.250 0.7498 0.00858 0.00311 -0.0270 0.3268 1.0000
5.500 0.7745 0.00897 0.00338 -0.0266 0.2912 1.0000
5.750 0.7988 0.00942 0.00370 -0.0262 0.2529 1.0000
6.000 0.8223 0.00998 0.00406 -0.0257 0.2083 1.0000
6.250 0.8461 0.01051 0.00448 -0.0253 0.1735 1.0000
6.500 0.8696 0.01107 0.00490 -0.0248 0.1404 1.0000
6.750 0.8927 0.01168 0.00538 -0.0243 0.1099 1.0000
7.000 0.9158 0.01228 0.00587 -0.0237 0.0854 1.0000
7.250 0.9389 0.01288 0.00640 -0.0232 0.0647 1.0000
7.500 0.9609 0.01360 0.00705 -0.0225 0.0454 1.0000
7.750 0.9826 0.01436 0.00777 -0.0217 0.0320 1.0000
8.000 1.0043 0.01508 0.00848 -0.0209 0.0239 1.0000
8.250 1.0254 0.01586 0.00926 -0.0201 0.0181 1.0000
8.500 1.0467 0.01658 0.01012 -0.0193 0.0145 1.0000
8.750 1.0624 0.01800 0.01163 -0.0177 0.0094 1.0000
9.000 1.0811 0.01896 0.01269 -0.0165 0.0076 1.0000
9.250 1.0957 0.02033 0.01415 -0.0149 0.0064 1.0000
9.500 1.1002 0.02278 0.01684 -0.0121 0.0058 1.0000
9.750 1.1172 0.02370 0.01786 -0.0109 0.0054 1.0000
10.000 1.1315 0.02487 0.01917 -0.0093 0.0050 1.0000
10.250 1.1464 0.02579 0.02019 -0.0080 0.0046 1.0000
10.500 1.1558 0.02713 0.02167 -0.0060 0.0043 1.0000
10.750 1.1592 0.02871 0.02340 -0.0033 0.0042 1.0000
11.000 1.1643 0.03004 0.02488 -0.0011 0.0039 1.0000
11.250 1.1651 0.03197 0.02697 0.0010 0.0038 1.0000
11.500 1.1653 0.03407 0.02924 0.0027 0.0038 1.0000
11.750 1.1660 0.03617 0.03147 0.0038 0.0036 1.0000
12.000 1.1630 0.03887 0.03434 0.0046 0.0036 1.0000
12.250 1.1609 0.04151 0.03710 0.0048 0.0034 1.0000
12.500 1.1533 0.04509 0.04085 0.0046 0.0033 1.0000
12.750 1.1450 0.04907 0.04503 0.0040 0.0033 1.0000
13.000 1.1321 0.05389 0.05004 0.0026 0.0032 1.0000
13.250 1.1136 0.05987 0.05623 0.0002 0.0032 1.0000
13.500 1.1101 0.06393 0.06043 -0.0017 0.0033 1.0000
13.750 1.0888 0.07114 0.06783 -0.0055 0.0032 1.0000
14.000 1.0815 0.07642 0.07326 -0.0084 0.0033 1.0000
14.250 1.0585 0.08500 0.08201 -0.0135 0.0032 1.0000
14.500 1.0439 0.09282 0.09006 -0.0180 0.0035 1.0000
14.750 1.0339 0.09961 0.09690 -0.0222 0.0033 1.0000
15.000 1.0163 0.10872 0.10615 -0.0275 0.0034 1.0000
15.250 0.9999 0.11777 0.11530 -0.0328 0.0033 1.0000
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Polar data table (+)
Polar graphs
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