MH 110 10.01% (mh110-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 110 10.01% (mh110-il) Reynolds number: 200,000 Max Cl/Cd: 56.33 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh110-il-200000.txt Download as CSV file: xf-mh110-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 110 10.01%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5437 0.09693 0.09401 0.0196 1.0000 0.0490
-9.250 -0.5508 0.09111 0.08822 0.0166 1.0000 0.0504
-6.500 -0.6837 0.03465 0.02920 0.0093 1.0000 0.0270
-6.250 -0.6672 0.03002 0.02364 0.0127 1.0000 0.0209
-6.000 -0.6455 0.02760 0.02095 0.0140 1.0000 0.0199
-5.750 -0.6250 0.02450 0.01750 0.0155 1.0000 0.0194
-5.500 -0.6018 0.02217 0.01489 0.0167 1.0000 0.0192
-5.250 -0.5775 0.02030 0.01283 0.0179 1.0000 0.0194
-5.000 -0.5531 0.01876 0.01116 0.0190 1.0000 0.0199
-4.750 -0.5307 0.01710 0.00944 0.0203 1.0000 0.0210
-4.500 -0.5103 0.01567 0.00801 0.0218 1.0000 0.0244
-4.250 -0.4869 0.01489 0.00720 0.0229 1.0000 0.0308
-4.000 -0.4696 0.01306 0.00563 0.0252 1.0000 0.0726
-3.750 -0.4535 0.01153 0.00494 0.0269 1.0000 0.2223
-3.500 -0.4363 0.01055 0.00463 0.0286 1.0000 0.3523
-3.250 -0.4199 0.00976 0.00440 0.0307 1.0000 0.4706
-3.000 -0.4001 0.00911 0.00424 0.0323 0.9933 0.5786
-2.750 -0.3555 0.00857 0.00417 0.0295 0.9261 0.7098
-2.500 -0.3174 0.00846 0.00415 0.0288 0.8594 0.7976
-2.250 -0.2844 0.00866 0.00421 0.0293 0.8041 0.8530
-2.000 -0.2475 0.00901 0.00431 0.0287 0.7575 0.8899
-1.750 -0.2094 0.00941 0.00441 0.0277 0.7167 0.9155
-1.500 -0.1658 0.00983 0.00452 0.0254 0.6781 0.9317
-1.250 -0.1215 0.01022 0.00461 0.0227 0.6434 0.9450
-1.000 -0.0777 0.01053 0.00466 0.0199 0.6113 0.9574
-0.750 -0.0337 0.01080 0.00466 0.0168 0.5817 0.9692
-0.500 0.0144 0.01096 0.00458 0.0128 0.5530 0.9790
-0.250 0.0625 0.01100 0.00439 0.0086 0.5266 0.9882
0.000 0.1097 0.01097 0.00417 0.0045 0.5023 0.9970
0.250 0.1412 0.01094 0.00397 0.0034 0.4825 1.0000
0.500 0.1632 0.01096 0.00384 0.0042 0.4662 1.0000
0.750 0.1856 0.01099 0.00376 0.0050 0.4503 1.0000
1.000 0.2084 0.01105 0.00371 0.0058 0.4357 1.0000
1.250 0.2314 0.01112 0.00368 0.0065 0.4223 1.0000
1.500 0.2547 0.01122 0.00367 0.0073 0.4095 1.0000
1.750 0.2783 0.01132 0.00370 0.0080 0.3971 1.0000
2.000 0.3021 0.01141 0.00374 0.0086 0.3853 1.0000
2.250 0.3261 0.01155 0.00382 0.0093 0.3747 1.0000
2.500 0.3502 0.01171 0.00391 0.0099 0.3655 1.0000
2.750 0.3743 0.01187 0.00404 0.0106 0.3567 1.0000
3.000 0.3986 0.01205 0.00421 0.0112 0.3481 1.0000
3.250 0.4227 0.01229 0.00435 0.0119 0.3408 1.0000
3.500 0.4471 0.01245 0.00456 0.0125 0.3326 1.0000
3.750 0.4713 0.01274 0.00478 0.0131 0.3267 1.0000
4.000 0.4959 0.01294 0.00507 0.0137 0.3199 1.0000
4.250 0.5203 0.01322 0.00531 0.0144 0.3145 1.0000
4.500 0.5448 0.01350 0.00565 0.0150 0.3086 1.0000
4.750 0.5693 0.01376 0.00596 0.0156 0.3029 1.0000
5.000 0.5937 0.01415 0.00632 0.0162 0.2985 1.0000
5.250 0.6182 0.01444 0.00676 0.0168 0.2934 1.0000
5.500 0.6427 0.01476 0.00711 0.0174 0.2885 1.0000
5.750 0.6671 0.01519 0.00754 0.0180 0.2842 1.0000
6.000 0.6915 0.01552 0.00808 0.0186 0.2791 1.0000
6.250 0.7159 0.01585 0.00845 0.0192 0.2743 1.0000
6.500 0.7400 0.01627 0.00895 0.0199 0.2693 1.0000
6.750 0.7640 0.01650 0.00931 0.0205 0.2625 1.0000
7.000 0.7879 0.01678 0.00961 0.0212 0.2558 1.0000
7.250 0.8116 0.01682 0.00977 0.0219 0.2469 1.0000
7.500 0.8349 0.01691 0.01003 0.0227 0.2373 1.0000
7.750 0.8583 0.01696 0.01014 0.0234 0.2278 1.0000
8.000 0.8817 0.01699 0.01027 0.0242 0.2178 1.0000
8.250 0.9049 0.01696 0.01044 0.0249 0.2054 1.0000
8.500 0.9282 0.01685 0.01048 0.0256 0.1865 1.0000
8.750 0.9514 0.01689 0.01062 0.0262 0.1458 1.0000
9.000 0.9578 0.01974 0.01278 0.0276 0.0543 1.0000
9.250 0.9658 0.02217 0.01523 0.0294 0.0341 1.0000
9.500 0.9723 0.02440 0.01755 0.0313 0.0258 1.0000
9.750 0.9805 0.02621 0.01947 0.0329 0.0212 1.0000
10.000 0.9779 0.02881 0.02220 0.0353 0.0192 1.0000
10.250 0.9848 0.03040 0.02393 0.0369 0.0170 1.0000
10.500 0.9882 0.03213 0.02579 0.0384 0.0155 1.0000
10.750 0.9821 0.03424 0.02799 0.0404 0.0144 1.0000
11.000 0.9775 0.03685 0.03070 0.0408 0.0140 1.0000
11.250 0.9752 0.03972 0.03366 0.0405 0.0138 1.0000
11.500 0.9742 0.04264 0.03668 0.0401 0.0135 1.0000
11.750 0.9738 0.04561 0.03975 0.0398 0.0134 1.0000
12.000 0.9687 0.04925 0.04347 0.0395 0.0127 1.0000
12.250 0.9672 0.05260 0.04696 0.0390 0.0127 1.0000
12.500 0.9582 0.05716 0.05168 0.0382 0.0123 1.0000
12.750 0.9529 0.06124 0.05593 0.0366 0.0123 1.0000
13.000 0.9504 0.06494 0.05976 0.0347 0.0125 1.0000
13.250 0.9348 0.07085 0.06587 0.0321 0.0123 1.0000
13.500 0.9328 0.07463 0.06977 0.0297 0.0126 1.0000
13.750 0.9113 0.08183 0.07715 0.0260 0.0123 1.0000
14.000 0.9068 0.08626 0.08170 0.0232 0.0125 1.0000
14.250 0.8929 0.09260 0.08819 0.0195 0.0125 1.0000
14.500 0.8816 0.09892 0.09465 0.0156 0.0127 1.0000
14.750 0.8674 0.10617 0.10206 0.0112 0.0129 1.0000
15.000 0.8496 0.11458 0.11061 0.0061 0.0130 1.0000
15.250 0.8170 0.12768 0.12397 -0.0016 0.0142 1.0000
15.500 0.7674 0.14707 0.14347 -0.0118 0.0158 1.0000
15.750 0.7450 0.16012 0.15644 -0.0171 0.0172 1.0000
16.000 0.7388 0.16810 0.16437 -0.0203 0.0177 1.0000
16.250 0.7379 0.17367 0.16992 -0.0224 0.0185 1.0000
16.500 0.7303 0.18617 0.18235 -0.0266 0.0260 1.0000
16.750 0.5715 0.17055 0.16721 -0.0190 0.0259 1.0000
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Polar data table (+)
Polar graphs
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