MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 100,000 Max Cl/Cd: 36.13 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh108-il-100000.txt Download as CSV file: xf-mh108-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 108 11.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7171 0.08168 0.07697 -0.0114 1.0000 0.0491
-10.750 -0.7357 0.07455 0.06982 -0.0161 1.0000 0.0484
-10.500 -0.7583 0.06831 0.06349 -0.0201 1.0000 0.0476
-10.250 -0.7806 0.06323 0.05829 -0.0216 1.0000 0.0465
-10.000 -0.8054 0.05886 0.05373 -0.0208 1.0000 0.0459
-9.750 -0.8248 0.05469 0.04931 -0.0189 1.0000 0.0454
-9.500 -0.8367 0.05065 0.04491 -0.0170 1.0000 0.0459
-9.250 -0.8423 0.04668 0.04052 -0.0149 1.0000 0.0465
-9.000 -0.8420 0.04291 0.03627 -0.0127 1.0000 0.0472
-8.750 -0.8368 0.03935 0.03217 -0.0105 1.0000 0.0482
-8.500 -0.8265 0.03640 0.02863 -0.0082 1.0000 0.0495
-8.250 -0.8107 0.03306 0.02526 -0.0072 1.0000 0.0529
-8.000 -0.7932 0.03148 0.02344 -0.0057 1.0000 0.0591
-7.750 -0.7744 0.02899 0.02083 -0.0043 1.0000 0.0654
-7.500 -0.7553 0.02723 0.01881 -0.0029 1.0000 0.0755
-7.250 -0.7358 0.02572 0.01727 -0.0015 1.0000 0.0889
-7.000 -0.7161 0.02448 0.01609 -0.0003 1.0000 0.1047
-6.750 -0.6960 0.02346 0.01507 0.0010 1.0000 0.1224
-6.500 -0.6753 0.02250 0.01398 0.0023 1.0000 0.1411
-6.250 -0.6538 0.02144 0.01305 0.0034 1.0000 0.1596
-6.000 -0.6322 0.02058 0.01223 0.0045 1.0000 0.1794
-5.750 -0.6104 0.01973 0.01137 0.0057 1.0000 0.2008
-5.500 -0.5888 0.01895 0.01072 0.0068 1.0000 0.2235
-5.250 -0.5674 0.01818 0.01006 0.0080 1.0000 0.2479
-5.000 -0.5464 0.01749 0.00948 0.0093 1.0000 0.2751
-4.750 -0.5260 0.01685 0.00896 0.0107 1.0000 0.3043
-4.500 -0.5065 0.01625 0.00854 0.0122 1.0000 0.3353
-4.250 -0.4883 0.01570 0.00819 0.0139 1.0000 0.3685
-4.000 -0.4721 0.01524 0.00791 0.0158 1.0000 0.4045
-3.750 -0.4603 0.01485 0.00776 0.0183 1.0000 0.4390
-3.500 -0.4393 0.01456 0.00769 0.0186 0.9935 0.4835
-3.250 -0.3830 0.01406 0.00752 0.0130 0.9692 0.5560
-3.000 -0.3317 0.01363 0.00738 0.0091 0.9428 0.6283
-2.750 -0.2855 0.01334 0.00731 0.0068 0.9137 0.6946
-2.500 -0.2466 0.01328 0.00734 0.0064 0.8820 0.7530
-2.250 -0.2134 0.01342 0.00745 0.0074 0.8494 0.8021
-2.000 -0.1787 0.01373 0.00763 0.0080 0.8174 0.8425
-1.750 -0.1395 0.01415 0.00787 0.0077 0.7866 0.8753
-1.500 -0.0943 0.01463 0.00809 0.0061 0.7568 0.9011
-1.250 -0.0440 0.01508 0.00827 0.0030 0.7275 0.9231
-1.000 0.0100 0.01544 0.00835 -0.0011 0.6991 0.9425
-0.750 0.0653 0.01568 0.00830 -0.0059 0.6724 0.9615
-0.500 0.1199 0.01575 0.00814 -0.0111 0.6462 0.9810
-0.250 0.1795 0.01554 0.00770 -0.0176 0.6211 0.9977
0.000 0.2032 0.01546 0.00747 -0.0176 0.6037 1.0000
0.250 0.2221 0.01547 0.00733 -0.0166 0.5884 1.0000
0.500 0.2418 0.01552 0.00726 -0.0156 0.5739 1.0000
0.750 0.2623 0.01559 0.00723 -0.0146 0.5601 1.0000
1.000 0.2833 0.01571 0.00724 -0.0137 0.5473 1.0000
1.250 0.3048 0.01585 0.00728 -0.0127 0.5359 1.0000
1.500 0.3266 0.01602 0.00734 -0.0118 0.5251 1.0000
1.750 0.3487 0.01622 0.00751 -0.0110 0.5135 1.0000
2.000 0.3709 0.01646 0.00773 -0.0101 0.5033 1.0000
2.250 0.3933 0.01671 0.00785 -0.0092 0.4948 1.0000
2.500 0.4160 0.01699 0.00817 -0.0084 0.4843 1.0000
2.750 0.4387 0.01731 0.00847 -0.0076 0.4756 1.0000
3.000 0.4615 0.01761 0.00872 -0.0067 0.4671 1.0000
3.250 0.4843 0.01799 0.00914 -0.0060 0.4581 1.0000
3.500 0.5074 0.01830 0.00937 -0.0050 0.4508 1.0000
3.750 0.5301 0.01873 0.00990 -0.0043 0.4415 1.0000
4.000 0.5534 0.01909 0.01019 -0.0034 0.4344 1.0000
4.250 0.5761 0.01953 0.01073 -0.0026 0.4254 1.0000
4.500 0.5991 0.01995 0.01117 -0.0017 0.4177 1.0000
4.750 0.6220 0.02036 0.01162 -0.0009 0.4093 1.0000
5.000 0.6446 0.02086 0.01219 0.0000 0.4011 1.0000
5.250 0.6680 0.02122 0.01252 0.0009 0.3931 1.0000
5.500 0.6899 0.02179 0.01325 0.0017 0.3842 1.0000
5.750 0.7141 0.02210 0.01346 0.0027 0.3769 1.0000
6.000 0.7353 0.02270 0.01426 0.0036 0.3669 1.0000
6.250 0.7580 0.02316 0.01476 0.0045 0.3584 1.0000
6.500 0.7811 0.02353 0.01517 0.0055 0.3494 1.0000
6.750 0.8021 0.02414 0.01594 0.0065 0.3394 1.0000
7.000 0.8256 0.02449 0.01625 0.0074 0.3307 1.0000
7.250 0.8477 0.02490 0.01676 0.0084 0.3205 1.0000
7.500 0.8682 0.02550 0.01753 0.0095 0.3098 1.0000
7.750 0.8907 0.02590 0.01794 0.0105 0.3001 1.0000
8.000 0.9142 0.02613 0.01815 0.0115 0.2900 1.0000
8.250 0.9335 0.02670 0.01891 0.0128 0.2783 1.0000
8.500 0.9536 0.02725 0.01958 0.0139 0.2672 1.0000
8.750 0.9755 0.02757 0.01991 0.0150 0.2564 1.0000
9.000 0.9996 0.02767 0.01993 0.0160 0.2458 1.0000
9.250 1.0172 0.02819 0.02065 0.0174 0.2335 1.0000
9.500 1.0351 0.02870 0.02131 0.0187 0.2213 1.0000
9.750 1.0531 0.02922 0.02192 0.0201 0.2093 1.0000
10.000 1.0709 0.02968 0.02244 0.0215 0.1973 1.0000
10.250 1.0882 0.03019 0.02298 0.0228 0.1854 1.0000
10.500 1.1043 0.03077 0.02357 0.0243 0.1732 1.0000
10.750 1.1192 0.03151 0.02427 0.0257 0.1611 1.0000
11.000 1.1313 0.03243 0.02519 0.0273 0.1488 1.0000
11.250 1.1376 0.03373 0.02668 0.0293 0.1377 1.0000
11.500 1.1418 0.03523 0.02831 0.0314 0.1271 1.0000
11.750 1.1457 0.03680 0.02991 0.0333 0.1174 1.0000
12.000 1.1507 0.03824 0.03120 0.0351 0.1076 1.0000
12.250 1.1381 0.04023 0.03349 0.0381 0.1018 1.0000
12.500 1.1387 0.04208 0.03521 0.0396 0.0941 1.0000
12.750 1.1249 0.04488 0.03829 0.0405 0.0896 1.0000
13.000 1.1276 0.04697 0.04017 0.0410 0.0822 1.0000
13.250 1.1115 0.05081 0.04438 0.0403 0.0792 1.0000
13.500 1.1010 0.05445 0.04818 0.0392 0.0753 1.0000
13.750 1.1022 0.05715 0.05073 0.0392 0.0696 1.0000
14.000 1.0844 0.06217 0.05603 0.0369 0.0677 1.0000
14.250 1.0668 0.06755 0.06164 0.0343 0.0659 1.0000
14.500 1.0508 0.07294 0.06721 0.0315 0.0641 1.0000
14.750 1.0597 0.07482 0.06885 0.0322 0.0585 1.0000
15.000 1.0374 0.08142 0.07569 0.0284 0.0580 1.0000
15.250 1.0146 0.08859 0.08306 0.0243 0.0580 1.0000
15.500 0.9879 0.09685 0.09150 0.0194 0.0583 1.0000
15.750 0.9606 0.10593 0.10076 0.0143 0.0589 1.0000
16.000 0.7551 0.17172 0.16635 -0.0207 0.0951 1.0000
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Polar data table (+)
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