MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: MH 102 16.99% (mh102-il) Reynolds number: 50,000 Max Cl/Cd: 5.54 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh102-il-50000.txt Download as CSV file: xf-mh102-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 102 16.99%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2848 0.11661 0.10928 -0.0231 1.0000 0.3323
-10.500 -0.2986 0.11588 0.10862 -0.0230 1.0000 0.3451
-10.250 -0.2801 0.11168 0.10439 -0.0223 1.0000 0.3622
-10.000 -0.2655 0.10791 0.10059 -0.0219 1.0000 0.3772
-9.750 -0.2616 0.10499 0.09770 -0.0214 1.0000 0.3901
-9.500 -0.2900 0.10546 0.09831 -0.0201 1.0000 0.4022
-9.250 -0.2730 0.10191 0.09473 -0.0193 1.0000 0.4206
-9.000 -0.2555 0.09838 0.09118 -0.0185 1.0000 0.4383
-8.750 -0.2404 0.09514 0.08793 -0.0178 1.0000 0.4545
-8.500 -0.2329 0.09249 0.08530 -0.0168 1.0000 0.4688
-8.250 -0.2339 0.09059 0.08348 -0.0152 1.0000 0.4841
-8.000 -0.2631 0.09135 0.08442 -0.0114 1.0000 0.4983
-7.750 -0.4787 0.07910 0.07293 -0.0156 1.0000 0.3268
-7.500 -0.5089 0.07677 0.07072 -0.0124 1.0000 0.3257
-7.250 -0.5428 0.07369 0.06775 -0.0100 1.0000 0.3244
-7.000 -0.5799 0.06957 0.06368 -0.0088 1.0000 0.3234
-6.750 -0.6176 0.06422 0.05829 -0.0089 1.0000 0.3242
-6.500 -0.6502 0.05783 0.05165 -0.0104 1.0000 0.3281
-6.250 -0.6290 0.06008 0.05404 -0.0055 1.0000 0.3390
-6.000 -0.6029 0.05736 0.05111 -0.0096 0.9903 0.3525
-5.750 -0.5796 0.05272 0.04603 -0.0167 0.9772 0.3659
-5.500 -0.5382 0.05217 0.04538 -0.0195 0.9643 0.3790
-5.250 -0.5023 0.05032 0.04332 -0.0234 0.9516 0.3902
-5.000 -0.4753 0.04740 0.03998 -0.0282 0.9386 0.4015
-4.750 -0.4436 0.04688 0.03945 -0.0291 0.9256 0.4105
-4.500 -0.4179 0.04463 0.03675 -0.0328 0.9131 0.4212
-4.250 -0.3744 0.04420 0.03632 -0.0354 0.9019 0.4316
-4.000 -0.3534 0.04268 0.03446 -0.0371 0.8892 0.4414
-3.750 -0.3252 0.04236 0.03413 -0.0375 0.8773 0.4498
-3.500 -0.2838 0.04130 0.03279 -0.0413 0.8672 0.4626
-3.250 -0.2684 0.04107 0.03253 -0.0401 0.8547 0.4707
-3.000 -0.2355 0.04044 0.03169 -0.0421 0.8446 0.4827
-2.750 -0.2109 0.04019 0.03135 -0.0423 0.8334 0.4941
-2.500 -0.1881 0.04001 0.03110 -0.0424 0.8233 0.5048
-2.250 -0.1575 0.03971 0.03064 -0.0437 0.8135 0.5191
-2.000 -0.1408 0.03988 0.03082 -0.0425 0.8034 0.5305
-1.750 -0.1091 0.03976 0.03065 -0.0435 0.7943 0.5458
-1.500 -0.0951 0.04003 0.03084 -0.0424 0.7850 0.5597
-1.250 -0.0673 0.04010 0.03089 -0.0428 0.7761 0.5779
-1.000 -0.0491 0.04047 0.03122 -0.0421 0.7676 0.5956
-0.750 -0.0325 0.04085 0.03162 -0.0411 0.7589 0.6145
-0.500 -0.0011 0.04105 0.03189 -0.0413 0.7517 0.6386
-0.250 -0.0006 0.04188 0.03276 -0.0386 0.7430 0.6575
0.000 0.0358 0.04196 0.03290 -0.0392 0.7359 0.6926
0.250 0.0329 0.04297 0.03402 -0.0359 0.7285 0.7169
0.500 0.0469 0.04349 0.03469 -0.0340 0.7212 0.7553
0.750 0.0768 0.04369 0.03512 -0.0328 0.7146 0.8139
1.000 0.0840 0.04485 0.03655 -0.0315 0.7071 0.8825
1.250 0.2470 0.04602 0.03756 -0.0565 0.6927 1.0000
1.500 0.2135 0.04712 0.03836 -0.0515 0.6870 1.0000
1.750 0.2502 0.04780 0.03878 -0.0533 0.6798 1.0000
2.000 0.2389 0.04968 0.04049 -0.0506 0.6737 1.0000
2.250 0.2415 0.05129 0.04196 -0.0493 0.6673 1.0000
2.500 0.2881 0.05204 0.04254 -0.0513 0.6593 1.0000
2.750 0.2678 0.05438 0.04479 -0.0484 0.6546 1.0000
3.000 0.2721 0.05617 0.04650 -0.0474 0.6490 1.0000
3.250 0.3138 0.05719 0.04739 -0.0488 0.6403 1.0000
3.500 0.3003 0.05959 0.04973 -0.0468 0.6369 1.0000
3.750 0.3001 0.06172 0.05181 -0.0459 0.6331 1.0000
4.000 0.3066 0.06384 0.05387 -0.0455 0.6302 1.0000
4.250 0.3374 0.06534 0.05530 -0.0461 0.6205 1.0000
4.500 0.2947 0.07040 0.06041 -0.0458 0.6566 1.0000
4.750 0.3449 0.07052 0.06042 -0.0458 0.6210 1.0000
5.000 0.3602 0.07335 0.06321 -0.0467 0.6226 1.0000
5.250 0.2872 0.08050 0.07050 -0.0477 0.7157 1.0000
5.500 0.2798 0.08060 0.07057 -0.0452 0.7023 1.0000
5.750 0.2955 0.08297 0.07290 -0.0455 0.6927 1.0000
6.000 0.3248 0.08578 0.07568 -0.0469 0.6798 1.0000
6.250 0.3222 0.08687 0.07676 -0.0454 0.6684 1.0000
6.500 0.3631 0.09119 0.08104 -0.0480 0.6595 1.0000
6.750 0.3583 0.09160 0.08145 -0.0462 0.6452 1.0000
7.000 0.3688 0.09407 0.08390 -0.0462 0.6370 1.0000
7.250 0.3927 0.09674 0.08657 -0.0470 0.6248 1.0000
7.500 0.3915 0.09826 0.08809 -0.0460 0.6135 1.0000
7.750 0.4320 0.10269 0.09253 -0.0482 0.6047 1.0000
8.000 0.4184 0.10309 0.09293 -0.0464 0.5927 1.0000
8.250 0.4512 0.10742 0.09726 -0.0481 0.5852 1.0000
8.500 0.4482 0.10826 0.09811 -0.0469 0.5717 1.0000
8.750 0.4623 0.11152 0.10139 -0.0475 0.5653 1.0000
9.000 0.4732 0.11350 0.10339 -0.0474 0.5528 1.0000
9.250 0.4771 0.11596 0.10586 -0.0474 0.5443 1.0000
9.500 0.4996 0.11900 0.10893 -0.0480 0.5337 1.0000
9.750 0.4979 0.12117 0.11112 -0.0479 0.5258 1.0000
10.000 0.5221 0.12445 0.11444 -0.0486 0.5153 1.0000
10.250 0.5177 0.12637 0.11637 -0.0484 0.5067 1.0000
10.500 0.5409 0.12977 0.11981 -0.0491 0.4976 1.0000
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Polar data table (+)
Polar graphs
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