MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 50,000 Max Cl/Cd: 32.89 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh60-il-50000-n5.txt Download as CSV file: xf-mh60-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 60 10.08%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5403 0.09566 0.08939 -0.0011 1.0000 0.0360
-9.000 -0.5457 0.08912 0.08294 -0.0058 1.0000 0.0350
-8.750 -0.5602 0.07873 0.07253 -0.0162 1.0000 0.0329
-8.500 -0.5678 0.07351 0.06733 -0.0202 1.0000 0.0327
-8.250 -0.5748 0.06857 0.06232 -0.0230 1.0000 0.0325
-8.000 -0.5786 0.06373 0.05735 -0.0254 1.0000 0.0323
-7.750 -0.5792 0.05903 0.05245 -0.0272 1.0000 0.0321
-7.500 -0.5768 0.05439 0.04751 -0.0285 1.0000 0.0321
-7.250 -0.5703 0.05002 0.04276 -0.0292 1.0000 0.0321
-7.000 -0.5603 0.04588 0.03817 -0.0294 1.0000 0.0323
-6.750 -0.5465 0.04226 0.03402 -0.0293 1.0000 0.0328
-6.500 -0.5312 0.03900 0.03051 -0.0291 1.0000 0.0344
-6.250 -0.5132 0.03669 0.02801 -0.0288 1.0000 0.0371
-6.000 -0.4940 0.03428 0.02519 -0.0281 1.0000 0.0397
-5.750 -0.4741 0.03188 0.02238 -0.0270 1.0000 0.0419
-5.500 -0.4546 0.02992 0.02006 -0.0255 1.0000 0.0442
-5.250 -0.4405 0.02832 0.01850 -0.0239 1.0000 0.0491
-5.000 -0.4257 0.02702 0.01693 -0.0217 1.0000 0.0556
-4.750 -0.4130 0.02569 0.01563 -0.0196 1.0000 0.0622
-4.500 -0.3994 0.02452 0.01439 -0.0175 1.0000 0.0748
-4.250 -0.3677 0.02289 0.01282 -0.0188 0.9896 0.1074
-4.000 -0.3318 0.02111 0.01157 -0.0214 0.9795 0.2057
-3.750 -0.2972 0.02021 0.01112 -0.0235 0.9691 0.3256
-3.500 -0.2638 0.01966 0.01080 -0.0249 0.9585 0.4182
-3.250 -0.2314 0.01922 0.01049 -0.0256 0.9477 0.4938
-3.000 -0.1992 0.01882 0.01019 -0.0261 0.9373 0.5657
-2.750 -0.1661 0.01848 0.01000 -0.0264 0.9277 0.6413
-2.500 -0.1331 0.01822 0.00988 -0.0263 0.9175 0.7220
-2.250 -0.0889 0.01807 0.00975 -0.0279 0.9088 0.8097
-2.000 -0.0261 0.01801 0.00947 -0.0334 0.9021 0.8886
-1.750 0.0358 0.01797 0.00913 -0.0394 0.8931 0.9453
-1.500 0.0966 0.01785 0.00869 -0.0458 0.8836 0.9906
-1.250 0.1265 0.01790 0.00850 -0.0467 0.8700 1.0000
-1.000 0.1468 0.01804 0.00845 -0.0456 0.8554 1.0000
-0.750 0.1672 0.01820 0.00841 -0.0444 0.8414 1.0000
-0.500 0.1877 0.01837 0.00842 -0.0431 0.8276 1.0000
-0.250 0.2084 0.01855 0.00845 -0.0418 0.8142 1.0000
0.000 0.2293 0.01873 0.00849 -0.0403 0.8009 1.0000
0.250 0.2504 0.01890 0.00853 -0.0389 0.7879 1.0000
0.500 0.2717 0.01909 0.00862 -0.0375 0.7744 1.0000
0.750 0.2931 0.01927 0.00871 -0.0361 0.7607 1.0000
1.000 0.3149 0.01945 0.00882 -0.0348 0.7470 1.0000
1.250 0.3367 0.01963 0.00894 -0.0334 0.7332 1.0000
1.500 0.3589 0.01980 0.00905 -0.0321 0.7193 1.0000
1.750 0.3813 0.01997 0.00917 -0.0308 0.7052 1.0000
2.000 0.4040 0.02012 0.00929 -0.0295 0.6909 1.0000
2.250 0.4269 0.02027 0.00943 -0.0283 0.6764 1.0000
2.500 0.4500 0.02041 0.00955 -0.0270 0.6616 1.0000
2.750 0.4732 0.02054 0.00966 -0.0257 0.6467 1.0000
3.000 0.4965 0.02066 0.00977 -0.0244 0.6315 1.0000
3.250 0.5199 0.02085 0.01001 -0.0234 0.6145 1.0000
3.500 0.5434 0.02103 0.01021 -0.0223 0.5973 1.0000
3.750 0.5670 0.02118 0.01038 -0.0211 0.5803 1.0000
4.000 0.5907 0.02133 0.01053 -0.0199 0.5632 1.0000
4.250 0.6145 0.02148 0.01072 -0.0187 0.5459 1.0000
4.500 0.6381 0.02176 0.01105 -0.0178 0.5262 1.0000
4.750 0.6617 0.02198 0.01129 -0.0167 0.5073 1.0000
5.000 0.6853 0.02224 0.01155 -0.0156 0.4883 1.0000
5.250 0.7086 0.02261 0.01200 -0.0147 0.4676 1.0000
5.500 0.7320 0.02293 0.01232 -0.0136 0.4481 1.0000
5.750 0.7548 0.02341 0.01286 -0.0127 0.4268 1.0000
6.000 0.7776 0.02386 0.01332 -0.0117 0.4065 1.0000
6.250 0.7999 0.02442 0.01398 -0.0108 0.3854 1.0000
6.500 0.8220 0.02499 0.01459 -0.0099 0.3649 1.0000
6.750 0.8437 0.02565 0.01530 -0.0090 0.3445 1.0000
7.000 0.8648 0.02636 0.01608 -0.0081 0.3240 1.0000
7.250 0.8857 0.02710 0.01684 -0.0072 0.3049 1.0000
7.500 0.9056 0.02796 0.01784 -0.0063 0.2847 1.0000
7.750 0.9253 0.02884 0.01883 -0.0054 0.2664 1.0000
8.000 0.9442 0.02978 0.01980 -0.0044 0.2485 1.0000
8.250 0.9622 0.03085 0.02102 -0.0035 0.2307 1.0000
8.500 0.9793 0.03196 0.02224 -0.0025 0.2137 1.0000
8.750 0.9956 0.03314 0.02351 -0.0014 0.1980 1.0000
9.000 1.0106 0.03439 0.02484 -0.0003 0.1828 1.0000
9.500 1.0362 0.03720 0.02790 0.0020 0.1545 1.0000
9.750 1.0467 0.03882 0.02965 0.0032 0.1416 1.0000
10.000 1.0544 0.04057 0.03154 0.0044 0.1295 1.0000
10.250 1.0600 0.04247 0.03358 0.0057 0.1185 1.0000
10.500 1.0636 0.04443 0.03561 0.0072 0.1093 1.0000
10.750 1.0637 0.04645 0.03768 0.0085 0.1010 1.0000
11.000 1.0625 0.04913 0.04060 0.0094 0.0934 1.0000
11.250 1.0641 0.05134 0.04271 0.0102 0.0869 1.0000
11.500 1.0579 0.05486 0.04661 0.0103 0.0812 1.0000
11.750 1.0554 0.05769 0.04947 0.0102 0.0759 1.0000
12.000 1.0500 0.06150 0.05347 0.0098 0.0720 1.0000
12.250 1.0399 0.06610 0.05836 0.0086 0.0688 1.0000
12.500 1.0312 0.07046 0.06287 0.0072 0.0658 1.0000
12.750 1.0300 0.07363 0.06595 0.0065 0.0620 1.0000
13.000 1.0128 0.08003 0.07264 0.0035 0.0610 1.0000
13.250 0.9932 0.08727 0.08012 -0.0003 0.0605 1.0000
13.500 0.9709 0.09556 0.08861 -0.0049 0.0605 1.0000
13.750 0.9458 0.10516 0.09834 -0.0104 0.0611 1.0000
14.000 0.9197 0.11581 0.10905 -0.0164 0.0618 1.0000
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Polar data table (+)
Polar graphs
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