MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 500,000 Max Cl/Cd: 95.2 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh120-il-500000-n5.txt Download as CSV file: xf-mh120-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4575 0.08283 0.08065 -0.0418 1.0000 0.0073
-9.750 -0.4677 0.07735 0.07521 -0.0443 1.0000 0.0072
-9.500 -0.4831 0.07081 0.06872 -0.0477 1.0000 0.0071
-9.250 -0.5183 0.05929 0.05720 -0.0571 1.0000 0.0072
-9.000 -0.5391 0.05160 0.04930 -0.0616 0.9917 0.0070
-8.750 -0.5484 0.04363 0.04098 -0.0642 0.9782 0.0070
-8.500 -0.5644 0.03373 0.03036 -0.0636 0.9646 0.0075
-8.250 -0.5504 0.02960 0.02567 -0.0638 0.9584 0.0084
-8.000 -0.5323 0.02719 0.02302 -0.0639 0.9505 0.0087
-7.750 -0.5037 0.02573 0.02139 -0.0655 0.9458 0.0091
-7.500 -0.4771 0.02401 0.01942 -0.0664 0.9387 0.0094
-7.250 -0.4451 0.02211 0.01726 -0.0683 0.9331 0.0097
-7.000 -0.4143 0.02050 0.01538 -0.0697 0.9255 0.0101
-6.750 -0.3804 0.01912 0.01374 -0.0716 0.9178 0.0107
-6.500 -0.3501 0.01799 0.01239 -0.0725 0.9079 0.0113
-6.250 -0.3197 0.01700 0.01120 -0.0733 0.8980 0.0119
-6.000 -0.2902 0.01602 0.01002 -0.0738 0.8877 0.0123
-5.750 -0.2631 0.01524 0.00909 -0.0738 0.8763 0.0126
-5.500 -0.2370 0.01473 0.00844 -0.0735 0.8644 0.0129
-5.250 -0.2125 0.01404 0.00760 -0.0729 0.8526 0.0132
-5.000 -0.1906 0.01313 0.00657 -0.0718 0.8401 0.0135
-4.750 -0.1692 0.01247 0.00580 -0.0705 0.8274 0.0138
-4.500 -0.1486 0.01189 0.00512 -0.0691 0.8147 0.0144
-4.250 -0.1269 0.01150 0.00465 -0.0679 0.8020 0.0151
-4.000 -0.1051 0.01116 0.00422 -0.0666 0.7896 0.0155
-3.750 -0.0833 0.01085 0.00381 -0.0653 0.7771 0.0156
-3.500 -0.0611 0.01058 0.00342 -0.0640 0.7651 0.0160
-3.250 -0.0384 0.01035 0.00310 -0.0629 0.7540 0.0163
-3.000 -0.0152 0.01016 0.00282 -0.0619 0.7433 0.0167
-2.750 0.0081 0.01000 0.00257 -0.0608 0.7331 0.0175
-2.500 0.0319 0.00987 0.00235 -0.0599 0.7229 0.0182
-2.250 0.0560 0.00977 0.00216 -0.0591 0.7133 0.0194
-2.000 0.0801 0.00969 0.00200 -0.0582 0.7042 0.0208
-1.750 0.1043 0.00960 0.00187 -0.0574 0.6950 0.0245
-1.500 0.1234 0.00908 0.00170 -0.0558 0.6861 0.1325
-1.250 0.1395 0.00838 0.00157 -0.0536 0.6778 0.3098
-1.000 0.1589 0.00798 0.00153 -0.0520 0.6694 0.4181
-0.750 0.1783 0.00770 0.00150 -0.0503 0.6612 0.5062
-0.500 0.1995 0.00754 0.00149 -0.0489 0.6525 0.5613
-0.250 0.2193 0.00735 0.00148 -0.0471 0.6448 0.6252
0.000 0.2400 0.00723 0.00147 -0.0455 0.6366 0.6744
0.250 0.2578 0.00680 0.00153 -0.0431 0.6284 0.8099
0.500 0.3225 0.00671 0.00162 -0.0514 0.6190 0.8899
0.750 0.3882 0.00680 0.00168 -0.0601 0.6089 0.9136
1.000 0.4364 0.00693 0.00177 -0.0647 0.5989 0.9299
1.250 0.4764 0.00708 0.00187 -0.0675 0.5879 0.9413
1.500 0.5106 0.00723 0.00196 -0.0689 0.5753 0.9502
1.750 0.5407 0.00738 0.00206 -0.0694 0.5636 0.9602
2.000 0.5728 0.00753 0.00216 -0.0704 0.5529 0.9675
2.250 0.6035 0.00766 0.00226 -0.0711 0.5424 0.9751
2.500 0.6360 0.00780 0.00238 -0.0723 0.5320 0.9815
2.750 0.6675 0.00796 0.00249 -0.0732 0.5184 0.9867
3.000 0.7011 0.00810 0.00259 -0.0746 0.5066 0.9908
3.250 0.7332 0.00825 0.00271 -0.0758 0.4935 0.9942
3.500 0.7674 0.00839 0.00283 -0.0774 0.4794 0.9976
3.750 0.8023 0.00853 0.00293 -0.0792 0.4618 1.0000
4.000 0.8224 0.00868 0.00304 -0.0777 0.4460 1.0000
4.250 0.8420 0.00885 0.00317 -0.0761 0.4280 1.0000
4.500 0.8616 0.00905 0.00332 -0.0745 0.4104 1.0000
4.750 0.8786 0.00936 0.00350 -0.0724 0.3757 1.0000
5.000 0.8957 0.00969 0.00371 -0.0703 0.3443 1.0000
5.250 0.9097 0.01020 0.00399 -0.0678 0.2988 1.0000
5.500 0.9251 0.01067 0.00429 -0.0655 0.2615 1.0000
5.750 0.9378 0.01130 0.00467 -0.0627 0.2153 1.0000
6.000 0.9512 0.01190 0.00509 -0.0601 0.1746 1.0000
6.250 0.9655 0.01245 0.00548 -0.0577 0.1411 1.0000
6.500 0.9768 0.01317 0.00596 -0.0548 0.1000 1.0000
6.750 0.9907 0.01374 0.00641 -0.0523 0.0752 1.0000
7.000 0.9942 0.01489 0.00722 -0.0481 0.0235 1.0000
7.250 1.0081 0.01545 0.00773 -0.0456 0.0122 1.0000
7.500 1.0215 0.01602 0.00831 -0.0430 0.0075 1.0000
7.750 1.0371 0.01645 0.00879 -0.0408 0.0070 1.0000
8.000 1.0488 0.01697 0.00939 -0.0379 0.0060 1.0000
8.250 1.0601 0.01745 0.00995 -0.0349 0.0057 1.0000
8.500 1.0696 0.01808 0.01067 -0.0317 0.0052 1.0000
8.750 1.0798 0.01872 0.01141 -0.0287 0.0051 1.0000
9.000 1.0905 0.01938 0.01214 -0.0260 0.0050 1.0000
9.250 1.1050 0.01985 0.01266 -0.0240 0.0047 1.0000
9.500 1.1150 0.02063 0.01352 -0.0214 0.0045 1.0000
9.750 1.1245 0.02148 0.01446 -0.0189 0.0045 1.0000
10.000 1.1337 0.02239 0.01548 -0.0165 0.0042 1.0000
10.250 1.1421 0.02339 0.01656 -0.0142 0.0040 1.0000
10.500 1.1494 0.02452 0.01778 -0.0119 0.0039 1.0000
10.750 1.1556 0.02578 0.01914 -0.0097 0.0039 1.0000
11.000 1.1617 0.02712 0.02058 -0.0077 0.0037 1.0000
11.250 1.1677 0.02853 0.02208 -0.0059 0.0035 1.0000
11.500 1.1713 0.03021 0.02386 -0.0041 0.0035 1.0000
11.750 1.1766 0.03183 0.02557 -0.0027 0.0035 1.0000
12.000 1.1772 0.03393 0.02777 -0.0011 0.0032 1.0000
12.250 1.1802 0.03592 0.02987 0.0001 0.0032 1.0000
12.500 1.1854 0.03775 0.03178 0.0009 0.0032 1.0000
12.750 1.1771 0.04101 0.03517 0.0023 0.0029 1.0000
13.000 1.1742 0.04382 0.03810 0.0031 0.0029 1.0000
13.250 1.1836 0.04544 0.03985 0.0034 0.0031 1.0000
13.500 1.1720 0.04937 0.04391 0.0042 0.0029 1.0000
13.750 1.1730 0.05200 0.04665 0.0044 0.0029 1.0000
14.000 1.1591 0.05651 0.05136 0.0050 0.0027 1.0000
14.250 1.1570 0.05974 0.05471 0.0049 0.0028 1.0000
14.500 1.1507 0.06359 0.05871 0.0046 0.0027 1.0000
14.750 1.1452 0.06755 0.06282 0.0039 0.0027 1.0000
15.000 1.1395 0.07162 0.06703 0.0031 0.0027 1.0000
15.250 1.1343 0.07590 0.07147 0.0016 0.0027 1.0000
15.500 1.1257 0.08066 0.07637 0.0002 0.0027 1.0000
15.750 1.1180 0.08567 0.08154 -0.0018 0.0027 1.0000
16.000 1.1058 0.09133 0.08735 -0.0038 0.0027 1.0000
16.250 1.0961 0.09683 0.09298 -0.0061 0.0027 1.0000
16.500 1.0837 0.10302 0.09931 -0.0088 0.0027 1.0000
16.750 1.0694 0.10997 0.10642 -0.0121 0.0027 1.0000
17.000 1.0599 0.11609 0.11267 -0.0152 0.0027 1.0000
17.250 1.0451 0.12345 0.12017 -0.0189 0.0027 1.0000
17.500 1.0330 0.13047 0.12731 -0.0225 0.0027 1.0000
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Polar data table (+)
Polar graphs
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