MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.29 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh120-il-1000000.txt Download as CSV file: xf-mh120-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4300 0.08398 0.08243 -0.0408 1.0000 0.0101
-9.500 -0.4370 0.07868 0.07716 -0.0429 1.0000 0.0101
-9.000 -0.4715 0.06047 0.05893 -0.0556 1.0000 0.0102
-8.750 -0.4895 0.05474 0.05307 -0.0604 0.9978 0.0101
-8.500 -0.4922 0.04807 0.04610 -0.0651 0.9893 0.0102
-8.250 -0.5189 0.03641 0.03387 -0.0670 0.9774 0.0106
-8.000 -0.5041 0.03257 0.02978 -0.0680 0.9731 0.0108
-7.750 -0.4849 0.03120 0.02836 -0.0680 0.9658 0.0111
-7.500 -0.4580 0.02996 0.02702 -0.0696 0.9619 0.0115
-7.250 -0.4362 0.02720 0.02400 -0.0701 0.9551 0.0121
-7.000 -0.4056 0.02543 0.02201 -0.0717 0.9496 0.0134
-6.250 -0.3140 0.01719 0.01270 -0.0755 0.9270 0.0138
-6.000 -0.2820 0.01530 0.01052 -0.0767 0.9179 0.0137
-5.750 -0.2523 0.01591 0.01099 -0.0770 0.9058 0.0149
-5.500 -0.2253 0.01519 0.01014 -0.0769 0.8942 0.0148
-5.250 -0.2015 0.01293 0.00767 -0.0762 0.8824 0.0151
-5.000 -0.1776 0.01192 0.00654 -0.0754 0.8701 0.0152
-4.750 -0.1583 0.01076 0.00527 -0.0737 0.8573 0.0159
-4.500 -0.1378 0.01022 0.00463 -0.0721 0.8441 0.0161
-4.250 -0.1171 0.00980 0.00412 -0.0705 0.8310 0.0162
-4.000 -0.0967 0.00943 0.00366 -0.0689 0.8175 0.0167
-3.750 -0.0756 0.00912 0.00326 -0.0673 0.8042 0.0168
-3.500 -0.0541 0.00886 0.00291 -0.0659 0.7914 0.0177
-3.250 -0.0320 0.00863 0.00260 -0.0646 0.7789 0.0183
-3.000 -0.0095 0.00844 0.00232 -0.0634 0.7672 0.0190
-2.750 0.0135 0.00828 0.00208 -0.0623 0.7561 0.0199
-2.500 0.0368 0.00817 0.00188 -0.0612 0.7450 0.0209
-2.250 0.0607 0.00807 0.00172 -0.0603 0.7343 0.0212
-2.000 0.0848 0.00798 0.00156 -0.0594 0.7243 0.0235
-1.750 0.1061 0.00769 0.00141 -0.0580 0.7149 0.0747
-1.500 0.1184 0.00678 0.00123 -0.0551 0.7054 0.3026
-1.250 0.1376 0.00640 0.00117 -0.0534 0.6961 0.4116
-1.000 0.1568 0.00611 0.00115 -0.0516 0.6874 0.5089
-0.750 0.1767 0.00587 0.00113 -0.0499 0.6785 0.5866
-0.500 0.1946 0.00563 0.00113 -0.0477 0.6701 0.6700
-0.250 0.2117 0.00543 0.00114 -0.0452 0.6617 0.7448
0.000 0.2308 0.00517 0.00116 -0.0432 0.6529 0.8334
0.250 0.3238 0.00506 0.00125 -0.0582 0.6424 0.9229
0.500 0.3754 0.00519 0.00132 -0.0636 0.6321 0.9378
0.750 0.4160 0.00533 0.00141 -0.0665 0.6209 0.9487
1.000 0.4506 0.00548 0.00151 -0.0680 0.6096 0.9576
1.250 0.4834 0.00564 0.00162 -0.0690 0.6000 0.9643
1.500 0.5154 0.00579 0.00173 -0.0700 0.5904 0.9714
1.750 0.5494 0.00592 0.00183 -0.0714 0.5806 0.9761
2.000 0.5853 0.00606 0.00192 -0.0732 0.5698 0.9798
2.250 0.6157 0.00623 0.00203 -0.0739 0.5589 0.9851
2.500 0.6530 0.00633 0.00211 -0.0761 0.5480 0.9873
2.750 0.6893 0.00643 0.00218 -0.0781 0.5361 0.9898
3.000 0.7250 0.00654 0.00226 -0.0800 0.5246 0.9927
3.250 0.7605 0.00667 0.00235 -0.0818 0.5109 0.9953
3.500 0.7967 0.00675 0.00239 -0.0839 0.4964 0.9975
3.750 0.8326 0.00683 0.00243 -0.0859 0.4817 0.9994
4.000 0.8588 0.00693 0.00250 -0.0857 0.4675 1.0000
4.250 0.8787 0.00707 0.00260 -0.0842 0.4499 1.0000
4.500 0.8978 0.00726 0.00270 -0.0825 0.4270 1.0000
4.750 0.9170 0.00745 0.00282 -0.0808 0.4051 1.0000
5.000 0.9337 0.00778 0.00299 -0.0786 0.3669 1.0000
5.250 0.9493 0.00817 0.00320 -0.0763 0.3244 1.0000
5.500 0.9606 0.00880 0.00352 -0.0732 0.2637 1.0000
5.750 0.9769 0.00921 0.00378 -0.0710 0.2323 1.0000
6.000 0.9913 0.00972 0.00409 -0.0685 0.1933 1.0000
6.250 1.0049 0.01027 0.00444 -0.0659 0.1532 1.0000
6.500 1.0188 0.01082 0.00481 -0.0633 0.1190 1.0000
6.750 1.0293 0.01156 0.00531 -0.0601 0.0767 1.0000
7.000 1.0325 0.01269 0.00609 -0.0556 0.0215 1.0000
7.250 1.0445 0.01335 0.00669 -0.0526 0.0086 1.0000
7.500 1.0600 0.01383 0.00723 -0.0502 0.0073 1.0000
7.750 1.0771 0.01420 0.00764 -0.0483 0.0072 1.0000
8.000 1.0925 0.01467 0.00816 -0.0460 0.0068 1.0000
8.250 1.1077 0.01513 0.00868 -0.0437 0.0063 1.0000
8.500 1.1207 0.01560 0.00920 -0.0410 0.0060 1.0000
8.750 1.1303 0.01609 0.00975 -0.0376 0.0059 1.0000
9.000 1.1397 0.01663 0.01035 -0.0343 0.0057 1.0000
9.250 1.1488 0.01724 0.01102 -0.0311 0.0055 1.0000
9.500 1.1582 0.01788 0.01172 -0.0280 0.0054 1.0000
9.750 1.1614 0.01891 0.01283 -0.0241 0.0049 1.0000
10.000 1.1709 0.01966 0.01366 -0.0214 0.0050 1.0000
10.250 1.1713 0.02098 0.01510 -0.0176 0.0049 1.0000
10.500 1.1767 0.02212 0.01634 -0.0148 0.0045 1.0000
11.000 1.1798 0.02516 0.01956 -0.0090 0.0046 1.0000
11.250 1.1915 0.02608 0.02056 -0.0075 0.0044 1.0000
11.500 1.1898 0.02810 0.02267 -0.0049 0.0045 1.0000
11.750 1.1974 0.02947 0.02413 -0.0033 0.0044 1.0000
12.000 1.2041 0.03096 0.02570 -0.0019 0.0043 1.0000
12.250 1.2006 0.03349 0.02834 0.0003 0.0045 1.0000
12.500 1.2069 0.03517 0.03013 0.0015 0.0044 1.0000
12.750 1.2089 0.03733 0.03240 0.0029 0.0043 1.0000
13.000 1.2094 0.03978 0.03499 0.0043 0.0042 1.0000
13.250 1.2115 0.04202 0.03735 0.0052 0.0042 1.0000
13.500 1.2089 0.04496 0.04045 0.0065 0.0043 1.0000
13.750 1.2084 0.04763 0.04323 0.0071 0.0043 1.0000
14.000 1.1990 0.05162 0.04742 0.0083 0.0044 1.0000
14.250 1.2021 0.05382 0.04970 0.0079 0.0043 1.0000
14.500 1.1975 0.05777 0.05375 0.0099 0.0048 1.0000
14.750 1.1752 0.06383 0.06007 0.0101 0.0047 1.0000
15.000 1.1908 0.06402 0.06027 0.0067 0.0041 1.0000
15.250 1.1804 0.06868 0.06506 0.0079 0.0050 1.0000
15.500 1.1614 0.07473 0.07135 0.0046 0.0042 1.0000
15.750 1.1395 0.08150 0.07832 0.0028 0.0044 1.0000
16.000 0.9785 0.08371 0.08070 0.0109 0.0049 1.0000
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Polar data table (+)
Polar graphs
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