MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 50,000 Max Cl/Cd: 32.62 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh120-il-50000.txt Download as CSV file: xf-mh120-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 120 11.57%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3756 0.11500 0.10807 -0.0246 1.0000 0.2551
-9.500 -0.3776 0.11230 0.10545 -0.0243 1.0000 0.2666
-9.250 -0.3912 0.11121 0.10447 -0.0244 1.0000 0.2773
-9.000 -0.3776 0.10726 0.10054 -0.0232 1.0000 0.2905
-8.750 -0.3728 0.10399 0.09733 -0.0222 1.0000 0.3042
-8.500 -0.3641 0.10050 0.09389 -0.0213 1.0000 0.3145
-8.250 -0.3638 0.09765 0.09112 -0.0203 1.0000 0.3265
-8.000 -0.3660 0.09511 0.08867 -0.0191 1.0000 0.3391
-7.750 -0.3697 0.09266 0.08632 -0.0177 1.0000 0.3523
-7.250 -0.3820 0.08833 0.08222 -0.0137 1.0000 0.3796
-7.000 -0.3903 0.08633 0.08035 -0.0111 1.0000 0.3936
-6.750 -0.3716 0.08199 0.07602 -0.0103 1.0000 0.3993
-5.500 -0.5420 0.05631 0.04987 -0.0225 1.0000 0.1615
-5.250 -0.5374 0.05167 0.04487 -0.0211 1.0000 0.1432
-5.000 -0.5321 0.04781 0.04046 -0.0192 1.0000 0.1305
-4.750 -0.5250 0.04436 0.03615 -0.0165 1.0000 0.1200
-4.500 -0.5124 0.04161 0.03320 -0.0146 1.0000 0.1164
-4.250 -0.4988 0.03899 0.03008 -0.0123 1.0000 0.1122
-4.000 -0.4834 0.03691 0.02728 -0.0099 1.0000 0.1086
-3.750 -0.4662 0.03534 0.02521 -0.0078 1.0000 0.1074
-3.500 -0.4485 0.03350 0.02324 -0.0064 1.0000 0.1097
-3.250 -0.4305 0.03216 0.02176 -0.0049 1.0000 0.1147
-3.000 -0.4106 0.03097 0.02027 -0.0034 1.0000 0.1173
-2.750 -0.3893 0.02992 0.01897 -0.0020 1.0000 0.1200
-2.500 -0.3670 0.02875 0.01783 -0.0011 1.0000 0.1262
-2.250 -0.3446 0.02806 0.01696 -0.0001 1.0000 0.1345
-2.000 -0.1946 0.02351 0.01607 -0.0188 1.0000 1.0000
-1.750 -0.1852 0.02375 0.01589 -0.0170 1.0000 1.0000
-1.500 -0.1742 0.02407 0.01582 -0.0154 1.0000 1.0000
-1.250 -0.1622 0.02445 0.01586 -0.0139 1.0000 1.0000
-1.000 -0.1494 0.02487 0.01598 -0.0126 1.0000 1.0000
-0.750 -0.1360 0.02535 0.01616 -0.0114 1.0000 1.0000
-0.500 -0.1078 0.02613 0.01661 -0.0132 0.9954 1.0000
-0.250 -0.0634 0.02718 0.01734 -0.0180 0.9840 1.0000
0.000 -0.0221 0.02818 0.01804 -0.0221 0.9730 1.0000
0.250 0.0151 0.02905 0.01869 -0.0254 0.9615 1.0000
0.500 0.0479 0.02986 0.01930 -0.0277 0.9502 1.0000
0.750 0.0805 0.03070 0.01996 -0.0300 0.9390 1.0000
1.000 0.1146 0.03160 0.02072 -0.0324 0.9281 1.0000
1.250 0.1531 0.03257 0.02155 -0.0355 0.9173 1.0000
1.500 0.1786 0.03334 0.02223 -0.0364 0.9058 1.0000
1.750 0.2041 0.03417 0.02297 -0.0372 0.8945 1.0000
2.000 0.2324 0.03505 0.02379 -0.0384 0.8833 1.0000
2.250 0.2646 0.03596 0.02466 -0.0402 0.8721 1.0000
2.500 0.2981 0.03686 0.02553 -0.0422 0.8609 1.0000
2.750 0.3190 0.03772 0.02637 -0.0421 0.8487 1.0000
3.000 0.3413 0.03865 0.02728 -0.0422 0.8366 1.0000
3.250 0.3663 0.03957 0.02822 -0.0426 0.8244 1.0000
3.500 0.3929 0.04049 0.02918 -0.0433 0.8118 1.0000
3.750 0.4206 0.04139 0.03011 -0.0440 0.7990 1.0000
4.000 0.4484 0.04227 0.03104 -0.0446 0.7856 1.0000
4.250 0.4763 0.04312 0.03196 -0.0451 0.7721 1.0000
4.500 0.5028 0.04397 0.03291 -0.0454 0.7579 1.0000
4.750 0.5280 0.04481 0.03384 -0.0454 0.7433 1.0000
5.000 0.5517 0.04568 0.03480 -0.0451 0.7282 1.0000
5.250 0.5750 0.04654 0.03577 -0.0447 0.7125 1.0000
5.500 0.5993 0.04734 0.03673 -0.0443 0.6966 1.0000
5.750 0.6274 0.04794 0.03748 -0.0441 0.6800 1.0000
6.000 0.6608 0.04823 0.03796 -0.0441 0.6635 1.0000
6.250 0.7061 0.04774 0.03775 -0.0448 0.6469 1.0000
6.500 0.7206 0.04868 0.03882 -0.0429 0.6282 1.0000
6.750 0.7471 0.04883 0.03918 -0.0416 0.6089 1.0000
7.000 0.8192 0.04580 0.03662 -0.0429 0.5910 1.0000
7.250 0.8558 0.04487 0.03597 -0.0418 0.5699 1.0000
7.500 0.9513 0.03952 0.03115 -0.0444 0.5446 1.0000
7.750 0.9996 0.03733 0.02928 -0.0436 0.5155 1.0000
8.000 1.0324 0.03612 0.02826 -0.0416 0.4838 1.0000
8.250 1.0757 0.03424 0.02643 -0.0404 0.4452 1.0000
8.500 1.0915 0.03414 0.02637 -0.0368 0.4092 1.0000
8.750 1.1077 0.03400 0.02617 -0.0332 0.3696 1.0000
9.000 1.1158 0.03421 0.02618 -0.0288 0.3289 1.0000
9.250 1.1139 0.03482 0.02650 -0.0234 0.2881 1.0000
9.500 1.1029 0.03588 0.02730 -0.0175 0.2515 1.0000
9.750 1.0867 0.03729 0.02842 -0.0112 0.2179 1.0000
10.000 1.0682 0.03907 0.02998 -0.0053 0.1875 1.0000
10.250 1.0516 0.04143 0.03205 -0.0004 0.1559 1.0000
10.500 1.0460 0.04433 0.03445 0.0030 0.1246 1.0000
10.750 1.0585 0.04741 0.03753 0.0051 0.1020 1.0000
11.000 1.0859 0.05060 0.04053 0.0054 0.0863 1.0000
11.250 1.0952 0.05376 0.04416 0.0073 0.0811 1.0000
11.500 1.1111 0.05721 0.04783 0.0084 0.0763 1.0000
11.750 1.1332 0.06202 0.05281 0.0083 0.0733 1.0000
12.000 1.1268 0.06553 0.05668 0.0108 0.0731 1.0000
12.250 1.1146 0.06923 0.06072 0.0132 0.0729 1.0000
12.500 1.0987 0.07316 0.06494 0.0152 0.0729 1.0000
12.750 1.0814 0.07746 0.06949 0.0164 0.0730 1.0000
13.000 1.0618 0.08205 0.07431 0.0168 0.0731 1.0000
13.250 1.0468 0.08687 0.07934 0.0167 0.0736 1.0000
13.500 0.9688 0.09581 0.08870 0.0112 0.0775 1.0000
13.750 0.9246 0.10607 0.09910 0.0050 0.0811 1.0000
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Polar data table (+)
Polar graphs
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