MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 115 11.06% (mh115-il) Reynolds number: 1,000,000 Max Cl/Cd: 158.67 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh115-il-1000000.txt Download as CSV file: xf-mh115-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 115 11.06%
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0644 0.09725 0.09562 -0.0814 0.9839 0.0101
-10.500 -0.0610 0.09352 0.09190 -0.0826 0.9791 0.0101
-10.250 -0.0535 0.08932 0.08770 -0.0849 0.9768 0.0102
-10.000 -0.0446 0.08509 0.08347 -0.0874 0.9748 0.0102
-9.750 -0.0379 0.08040 0.07879 -0.0897 0.9731 0.0104
-9.500 -0.0298 0.07740 0.07579 -0.0907 0.9678 0.0105
-9.250 -0.0195 0.07395 0.07235 -0.0926 0.9631 0.0106
-9.000 -0.0059 0.07020 0.06859 -0.0956 0.9603 0.0109
-8.750 -0.0924 0.08169 0.08002 -0.0917 0.9734 0.0105
-8.500 -0.0815 0.07883 0.07717 -0.0937 0.9671 0.0106
-8.250 -0.0666 0.07569 0.07403 -0.0969 0.9619 0.0108
-8.000 -0.0495 0.07220 0.07053 -0.1012 0.9560 0.0110
-7.750 -0.0286 0.06805 0.06637 -0.1072 0.9494 0.0113
-7.500 -0.0005 0.06297 0.06126 -0.1163 0.9434 0.0118
-7.250 0.0238 0.05648 0.05471 -0.1272 0.9297 0.0126
-7.000 0.0372 0.04708 0.04522 -0.1404 0.9065 0.0131
-6.750 0.0049 0.01921 0.01576 -0.1635 0.8728 0.0078
-6.500 0.0246 0.01506 0.01109 -0.1646 0.8627 0.0068
-6.250 0.0498 0.01267 0.00821 -0.1650 0.8544 0.0063
-6.000 0.0764 0.01157 0.00687 -0.1650 0.8456 0.0061
-5.750 0.1037 0.01081 0.00594 -0.1651 0.8376 0.0061
-5.500 0.1311 0.01019 0.00517 -0.1651 0.8291 0.0062
-5.250 0.1588 0.00970 0.00457 -0.1652 0.8210 0.0062
-5.000 0.1865 0.00928 0.00404 -0.1652 0.8128 0.0064
-4.750 0.2146 0.00892 0.00359 -0.1652 0.8047 0.0067
-4.500 0.2425 0.00862 0.00318 -0.1652 0.7967 0.0071
-4.250 0.2707 0.00836 0.00284 -0.1652 0.7887 0.0078
-4.000 0.2988 0.00805 0.00244 -0.1652 0.7806 0.0107
-3.750 0.3271 0.00775 0.00219 -0.1653 0.7726 0.0232
-3.500 0.3548 0.00765 0.00205 -0.1653 0.7648 0.0301
-3.250 0.3830 0.00753 0.00192 -0.1653 0.7568 0.0377
-3.000 0.4108 0.00741 0.00180 -0.1653 0.7491 0.0518
-2.750 0.4391 0.00723 0.00171 -0.1655 0.7413 0.0768
-2.500 0.4669 0.00712 0.00163 -0.1655 0.7337 0.1059
-2.250 0.4952 0.00698 0.00157 -0.1656 0.7259 0.1365
-2.000 0.5230 0.00691 0.00152 -0.1656 0.7183 0.1676
-1.750 0.5513 0.00680 0.00148 -0.1658 0.7106 0.2034
-1.500 0.5790 0.00673 0.00146 -0.1658 0.7030 0.2416
-1.250 0.6073 0.00662 0.00145 -0.1659 0.6953 0.2890
-1.000 0.6350 0.00656 0.00145 -0.1659 0.6877 0.3395
-0.750 0.6633 0.00646 0.00146 -0.1661 0.6799 0.3900
-0.500 0.6909 0.00643 0.00149 -0.1661 0.6721 0.4388
-0.250 0.7190 0.00636 0.00152 -0.1662 0.6641 0.4902
0.000 0.7465 0.00634 0.00157 -0.1661 0.6562 0.5418
0.250 0.7745 0.00629 0.00162 -0.1661 0.6480 0.5950
0.500 0.8018 0.00628 0.00168 -0.1660 0.6398 0.6465
0.750 0.8292 0.00625 0.00175 -0.1659 0.6312 0.6981
1.000 0.8560 0.00624 0.00183 -0.1657 0.6228 0.7505
1.250 0.8821 0.00622 0.00191 -0.1653 0.6138 0.8048
1.500 0.9062 0.00617 0.00199 -0.1643 0.6051 0.8694
1.750 0.9264 0.00607 0.00199 -0.1624 0.5959 1.0000
2.000 0.9541 0.00616 0.00205 -0.1624 0.5862 1.0000
2.250 0.9812 0.00629 0.00212 -0.1623 0.5764 1.0000
2.750 1.0349 0.00655 0.00228 -0.1619 0.5549 1.0000
3.000 1.0615 0.00669 0.00237 -0.1617 0.5438 1.0000
3.250 1.0877 0.00686 0.00247 -0.1614 0.5319 1.0000
3.500 1.1135 0.00703 0.00259 -0.1611 0.5191 1.0000
3.750 1.1396 0.00720 0.00271 -0.1608 0.5060 1.0000
4.000 1.1652 0.00739 0.00284 -0.1604 0.4920 1.0000
4.250 1.1906 0.00759 0.00299 -0.1600 0.4775 1.0000
4.500 1.2155 0.00781 0.00315 -0.1595 0.4620 1.0000
4.750 1.2399 0.00806 0.00333 -0.1590 0.4451 1.0000
5.250 1.2880 0.00860 0.00372 -0.1577 0.4109 1.0000
5.500 1.3116 0.00889 0.00394 -0.1570 0.3927 1.0000
5.750 1.3350 0.00919 0.00417 -0.1563 0.3757 1.0000
6.000 1.3582 0.00948 0.00441 -0.1555 0.3601 1.0000
6.250 1.3808 0.00981 0.00467 -0.1547 0.3431 1.0000
6.500 1.4033 0.01014 0.00494 -0.1538 0.3276 1.0000
6.750 1.4252 0.01048 0.00523 -0.1529 0.3114 1.0000
7.000 1.4466 0.01085 0.00553 -0.1518 0.2954 1.0000
7.250 1.4679 0.01120 0.00583 -0.1508 0.2812 1.0000
7.500 1.4884 0.01159 0.00616 -0.1496 0.2662 1.0000
7.750 1.5077 0.01199 0.00651 -0.1482 0.2509 1.0000
8.000 1.5261 0.01238 0.00686 -0.1466 0.2376 1.0000
8.250 1.5433 0.01280 0.00724 -0.1447 0.2237 1.0000
8.500 1.5598 0.01326 0.00764 -0.1428 0.2099 1.0000
8.750 1.5759 0.01374 0.00808 -0.1409 0.1963 1.0000
9.000 1.5899 0.01431 0.00858 -0.1387 0.1800 1.0000
9.250 1.6024 0.01499 0.00916 -0.1362 0.1623 1.0000
9.500 1.6148 0.01567 0.00977 -0.1338 0.1460 1.0000
9.750 1.6276 0.01634 0.01039 -0.1316 0.1329 1.0000
10.000 1.6390 0.01710 0.01109 -0.1291 0.1187 1.0000
10.250 1.6497 0.01791 0.01185 -0.1267 0.1057 1.0000
10.500 1.6599 0.01878 0.01266 -0.1243 0.0942 1.0000
10.750 1.6700 0.01968 0.01352 -0.1219 0.0842 1.0000
11.000 1.6806 0.02057 0.01440 -0.1197 0.0758 1.0000
11.250 1.6903 0.02155 0.01537 -0.1175 0.0676 1.0000
11.500 1.6986 0.02266 0.01645 -0.1152 0.0597 1.0000
11.750 1.7063 0.02384 0.01762 -0.1130 0.0523 1.0000
12.000 1.7151 0.02500 0.01878 -0.1110 0.0462 1.0000
12.250 1.7219 0.02634 0.02011 -0.1089 0.0399 1.0000
12.500 1.7270 0.02786 0.02163 -0.1068 0.0337 1.0000
12.750 1.7308 0.02954 0.02331 -0.1047 0.0275 1.0000
13.000 1.7339 0.03137 0.02514 -0.1027 0.0221 1.0000
13.250 1.7363 0.03332 0.02710 -0.1008 0.0177 1.0000
13.500 1.7388 0.03534 0.02916 -0.0991 0.0145 1.0000
13.750 1.7421 0.03737 0.03124 -0.0976 0.0121 1.0000
14.000 1.7449 0.03953 0.03346 -0.0963 0.0103 1.0000
14.250 1.7462 0.04192 0.03589 -0.0950 0.0086 1.0000
14.500 1.7485 0.04429 0.03834 -0.0939 0.0072 1.0000
14.750 1.7491 0.04695 0.04107 -0.0930 0.0060 1.0000
15.000 1.7469 0.05002 0.04420 -0.0921 0.0046 1.0000
15.250 1.7440 0.05327 0.04754 -0.0914 0.0033 1.0000
15.500 1.7410 0.05669 0.05105 -0.0910 0.0025 1.0000
15.750 1.7351 0.06062 0.05508 -0.0907 0.0019 1.0000
16.000 1.7328 0.06418 0.05875 -0.0907 0.0017 1.0000
16.250 1.7287 0.06810 0.06278 -0.0908 0.0016 1.0000
16.500 1.7227 0.07242 0.06721 -0.0912 0.0014 1.0000
16.750 1.7147 0.07720 0.07212 -0.0919 0.0013 1.0000
17.000 1.7030 0.08270 0.07777 -0.0930 0.0012 1.0000
17.250 1.6972 0.08739 0.08258 -0.0940 0.0012 1.0000
17.500 1.6904 0.09237 0.08768 -0.0953 0.0012 1.0000
17.750 1.6826 0.09765 0.09309 -0.0969 0.0011 1.0000
18.000 1.6732 0.10327 0.09885 -0.0988 0.0011 1.0000
18.250 1.6635 0.10906 0.10476 -0.1009 0.0011 1.0000
18.500 1.6545 0.11480 0.11062 -0.1031 0.0011 1.0000
18.750 1.6425 0.12122 0.11717 -0.1058 0.0010 1.0000
19.000 1.6318 0.12745 0.12353 -0.1087 0.0010 1.0000
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Polar data table (+)
Polar graphs
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