MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 50,000 Max Cl/Cd: 35.49 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh42-il-50000-n5.txt Download as CSV file: xf-mh42-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5097 0.11913 0.11219 0.0005 1.0000 0.0413
-10.000 -0.5077 0.11468 0.10779 -0.0017 1.0000 0.0394
-9.500 -0.5119 0.10420 0.09744 -0.0096 1.0000 0.0349
-9.250 -0.5082 0.10009 0.09338 -0.0108 1.0000 0.0345
-9.000 -0.5058 0.09591 0.08926 -0.0125 1.0000 0.0340
-8.750 -0.5047 0.09158 0.08500 -0.0146 1.0000 0.0337
-8.500 -0.5041 0.08730 0.08079 -0.0170 1.0000 0.0332
-8.250 -0.5062 0.08245 0.07602 -0.0201 1.0000 0.0329
-8.000 -0.5095 0.07752 0.07117 -0.0239 1.0000 0.0324
-7.750 -0.5115 0.07235 0.06601 -0.0275 1.0000 0.0320
-7.500 -0.5134 0.06711 0.06073 -0.0305 1.0000 0.0316
-7.250 -0.5132 0.06222 0.05573 -0.0329 1.0000 0.0312
-7.000 -0.5111 0.05733 0.05067 -0.0347 1.0000 0.0309
-6.750 -0.5063 0.05258 0.04556 -0.0358 1.0000 0.0308
-6.500 -0.4982 0.04816 0.04077 -0.0363 1.0000 0.0313
-6.250 -0.4872 0.04403 0.03617 -0.0363 1.0000 0.0324
-6.000 -0.4731 0.04031 0.03186 -0.0357 1.0000 0.0340
-5.750 -0.4562 0.03721 0.02818 -0.0348 1.0000 0.0353
-5.500 -0.4401 0.03418 0.02495 -0.0340 1.0000 0.0375
-5.250 -0.4211 0.03171 0.02217 -0.0328 1.0000 0.0393
-5.000 -0.4011 0.02942 0.01954 -0.0313 1.0000 0.0420
-4.750 -0.3803 0.02764 0.01734 -0.0298 1.0000 0.0479
-4.500 -0.3621 0.02599 0.01569 -0.0284 1.0000 0.0560
-4.250 -0.3428 0.02435 0.01393 -0.0266 1.0000 0.0649
-4.000 -0.3243 0.02316 0.01269 -0.0251 1.0000 0.0830
-3.500 -0.2865 0.02057 0.01034 -0.0226 1.0000 0.1683
-3.250 -0.2700 0.01956 0.00975 -0.0214 1.0000 0.2531
-3.000 -0.2543 0.01871 0.00934 -0.0199 1.0000 0.3521
-2.750 -0.2343 0.01787 0.00907 -0.0188 0.9960 0.4840
-2.500 -0.2046 0.01714 0.00900 -0.0183 0.9843 0.6597
-2.250 -0.1617 0.01683 0.00892 -0.0192 0.9765 0.8386
-2.000 -0.0773 0.01671 0.00832 -0.0293 0.9766 0.9833
-1.750 -0.0279 0.01677 0.00795 -0.0343 0.9657 1.0000
-1.500 0.0152 0.01685 0.00768 -0.0381 0.9526 1.0000
-1.250 0.0569 0.01692 0.00744 -0.0413 0.9394 1.0000
-1.000 0.0954 0.01702 0.00729 -0.0438 0.9256 1.0000
-0.750 0.1314 0.01712 0.00719 -0.0457 0.9115 1.0000
-0.500 0.1649 0.01724 0.00712 -0.0470 0.8970 1.0000
-0.250 0.1960 0.01738 0.00711 -0.0478 0.8824 1.0000
0.000 0.2252 0.01753 0.00713 -0.0481 0.8677 1.0000
0.250 0.2528 0.01769 0.00719 -0.0480 0.8532 1.0000
0.500 0.2793 0.01786 0.00726 -0.0476 0.8387 1.0000
0.750 0.3049 0.01804 0.00737 -0.0471 0.8245 1.0000
1.000 0.3299 0.01824 0.00749 -0.0463 0.8102 1.0000
1.250 0.3545 0.01843 0.00764 -0.0455 0.7960 1.0000
1.500 0.3788 0.01863 0.00783 -0.0446 0.7818 1.0000
1.750 0.4029 0.01884 0.00800 -0.0436 0.7676 1.0000
2.000 0.4269 0.01904 0.00819 -0.0426 0.7533 1.0000
2.250 0.4509 0.01925 0.00840 -0.0416 0.7390 1.0000
2.500 0.4752 0.01946 0.00861 -0.0405 0.7244 1.0000
2.750 0.4996 0.01966 0.00889 -0.0395 0.7097 1.0000
3.000 0.5240 0.01986 0.00912 -0.0385 0.6948 1.0000
3.250 0.5476 0.02011 0.00943 -0.0374 0.6783 1.0000
3.500 0.5714 0.02034 0.00974 -0.0364 0.6614 1.0000
3.750 0.5954 0.02055 0.01007 -0.0352 0.6444 1.0000
4.000 0.6196 0.02073 0.01031 -0.0340 0.6273 1.0000
4.250 0.6431 0.02097 0.01066 -0.0329 0.6080 1.0000
4.500 0.6667 0.02117 0.01095 -0.0317 0.5882 1.0000
4.750 0.6901 0.02138 0.01127 -0.0304 0.5669 1.0000
5.000 0.7136 0.02156 0.01161 -0.0290 0.5448 1.0000
5.250 0.7362 0.02181 0.01198 -0.0277 0.5195 1.0000
5.500 0.7587 0.02206 0.01233 -0.0263 0.4926 1.0000
5.750 0.7807 0.02234 0.01268 -0.0249 0.4634 1.0000
6.000 0.8019 0.02272 0.01314 -0.0234 0.4306 1.0000
6.250 0.8224 0.02317 0.01361 -0.0219 0.3954 1.0000
6.500 0.8417 0.02376 0.01431 -0.0204 0.3567 1.0000
6.750 0.8597 0.02453 0.01503 -0.0189 0.3157 1.0000
7.000 0.8763 0.02549 0.01592 -0.0174 0.2743 1.0000
7.250 0.8915 0.02668 0.01700 -0.0159 0.2338 1.0000
7.500 0.9056 0.02806 0.01828 -0.0145 0.1965 1.0000
7.750 0.9182 0.02963 0.01973 -0.0130 0.1644 1.0000
8.000 0.9303 0.03136 0.02137 -0.0116 0.1375 1.0000
8.250 0.9420 0.03315 0.02315 -0.0101 0.1138 1.0000
8.750 0.9650 0.03710 0.02711 -0.0071 0.0831 1.0000
9.000 0.9751 0.03909 0.02914 -0.0058 0.0714 1.0000
9.250 0.9911 0.04145 0.03191 -0.0043 0.0631 1.0000
9.500 1.0044 0.04398 0.03460 -0.0030 0.0565 1.0000
9.750 1.0121 0.04621 0.03703 -0.0017 0.0501 1.0000
10.000 1.0218 0.04919 0.04019 -0.0004 0.0461 1.0000
10.250 1.0278 0.05271 0.04418 0.0011 0.0435 1.0000
10.500 1.0267 0.05613 0.04794 0.0026 0.0415 1.0000
10.750 1.0219 0.05932 0.05135 0.0037 0.0395 1.0000
11.000 1.0167 0.06246 0.05462 0.0041 0.0378 1.0000
11.250 1.0096 0.06626 0.05846 0.0041 0.0361 1.0000
11.500 0.9950 0.07085 0.06335 0.0030 0.0358 1.0000
11.750 0.9789 0.07609 0.06883 0.0010 0.0356 1.0000
12.000 0.9624 0.08189 0.07484 -0.0018 0.0357 1.0000
12.250 0.9454 0.08831 0.08141 -0.0053 0.0359 1.0000
12.500 0.9292 0.09517 0.08839 -0.0093 0.0361 1.0000
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Polar data table (+)
Polar graphs
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