MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 38 9.68% (mh38-il) Reynolds number: 500,000 Max Cl/Cd: 114.53 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh38-il-500000-n5.txt Download as CSV file: xf-mh38-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 38 9.68%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3354 0.08149 0.07931 -0.0476 0.9595 0.0031
-8.750 -0.3308 0.06996 0.06777 -0.0608 0.9283 0.0029
-8.500 -0.4459 0.03367 0.03079 -0.0888 0.8594 0.0024
-8.000 -0.4266 0.02407 0.02009 -0.0924 0.8345 0.0024
-7.750 -0.4083 0.02129 0.01684 -0.0927 0.8249 0.0024
-7.500 -0.3872 0.01923 0.01438 -0.0928 0.8165 0.0024
-7.250 -0.3643 0.01751 0.01232 -0.0927 0.8081 0.0025
-7.000 -0.3400 0.01625 0.01080 -0.0926 0.8006 0.0026
-6.750 -0.3148 0.01523 0.00955 -0.0925 0.7932 0.0027
-6.500 -0.2889 0.01439 0.00851 -0.0925 0.7864 0.0028
-6.250 -0.2627 0.01367 0.00761 -0.0924 0.7795 0.0030
-6.000 -0.2360 0.01301 0.00676 -0.0923 0.7732 0.0034
-5.750 -0.2091 0.01244 0.00602 -0.0922 0.7667 0.0037
-5.500 -0.1819 0.01196 0.00540 -0.0922 0.7608 0.0042
-5.250 -0.1548 0.01139 0.00471 -0.0921 0.7546 0.0055
-5.000 -0.1274 0.01102 0.00423 -0.0921 0.7490 0.0072
-4.750 -0.0998 0.01062 0.00382 -0.0921 0.7431 0.0122
-4.500 -0.0724 0.01030 0.00350 -0.0921 0.7376 0.0214
-4.250 -0.0448 0.01002 0.00319 -0.0922 0.7322 0.0315
-4.000 -0.0170 0.00977 0.00293 -0.0922 0.7266 0.0420
-3.750 0.0108 0.00957 0.00270 -0.0922 0.7216 0.0533
-3.500 0.0388 0.00937 0.00251 -0.0923 0.7161 0.0660
-3.250 0.0667 0.00920 0.00233 -0.0923 0.7109 0.0802
-3.000 0.0947 0.00906 0.00217 -0.0924 0.7058 0.0932
-2.750 0.1228 0.00892 0.00201 -0.0925 0.7005 0.1063
-2.250 0.1789 0.00866 0.00178 -0.0926 0.6903 0.1429
-2.000 0.2069 0.00854 0.00169 -0.0927 0.6850 0.1658
-1.750 0.2349 0.00843 0.00160 -0.0927 0.6801 0.1885
-1.500 0.2630 0.00830 0.00153 -0.0928 0.6746 0.2184
-1.250 0.2909 0.00819 0.00147 -0.0929 0.6695 0.2508
-1.000 0.3189 0.00807 0.00143 -0.0930 0.6644 0.2873
-0.750 0.3468 0.00794 0.00140 -0.0931 0.6589 0.3329
-0.500 0.3746 0.00782 0.00139 -0.0932 0.6539 0.3830
-0.250 0.4025 0.00768 0.00139 -0.0933 0.6482 0.4360
0.000 0.4302 0.00756 0.00140 -0.0933 0.6427 0.4937
0.250 0.4577 0.00741 0.00143 -0.0933 0.6373 0.5588
0.500 0.4849 0.00726 0.00147 -0.0933 0.6314 0.6297
0.750 0.5113 0.00709 0.00152 -0.0929 0.6259 0.7105
1.000 0.5352 0.00683 0.00159 -0.0920 0.6198 0.8161
1.250 0.5634 0.00659 0.00159 -0.0916 0.6139 0.9662
1.500 0.5948 0.00663 0.00161 -0.0924 0.6071 1.0000
1.750 0.6224 0.00672 0.00164 -0.0923 0.6005 1.0000
2.000 0.6503 0.00679 0.00169 -0.0924 0.5930 1.0000
2.250 0.6778 0.00689 0.00177 -0.0923 0.5856 1.0000
2.500 0.7055 0.00697 0.00183 -0.0923 0.5771 1.0000
2.750 0.7331 0.00707 0.00191 -0.0923 0.5685 1.0000
3.250 0.7878 0.00729 0.00211 -0.0922 0.5492 1.0000
3.500 0.8151 0.00740 0.00221 -0.0921 0.5388 1.0000
3.750 0.8421 0.00754 0.00233 -0.0920 0.5276 1.0000
4.000 0.8690 0.00769 0.00246 -0.0919 0.5148 1.0000
4.250 0.8957 0.00785 0.00263 -0.0917 0.5002 1.0000
4.500 0.9220 0.00805 0.00280 -0.0915 0.4834 1.0000
4.750 0.9478 0.00828 0.00299 -0.0912 0.4638 1.0000
5.000 0.9730 0.00857 0.00320 -0.0909 0.4388 1.0000
5.250 0.9972 0.00895 0.00347 -0.0904 0.4073 1.0000
5.500 1.0192 0.00953 0.00383 -0.0896 0.3578 1.0000
5.750 1.0404 0.01020 0.00429 -0.0888 0.3065 1.0000
6.000 1.0622 0.01081 0.00472 -0.0880 0.2653 1.0000
6.250 1.0817 0.01163 0.00527 -0.0870 0.2113 1.0000
6.500 1.0990 0.01263 0.00594 -0.0857 0.1497 1.0000
6.750 1.1149 0.01373 0.00669 -0.0842 0.0904 1.0000
7.000 1.1309 0.01477 0.00747 -0.0827 0.0464 1.0000
7.250 1.1479 0.01567 0.00821 -0.0812 0.0215 1.0000
7.500 1.1668 0.01636 0.00886 -0.0800 0.0116 1.0000
7.750 1.1853 0.01706 0.00956 -0.0788 0.0067 1.0000
8.000 1.2039 0.01772 0.01032 -0.0774 0.0048 1.0000
8.250 1.2198 0.01855 0.01121 -0.0758 0.0037 1.0000
8.500 1.2336 0.01947 0.01225 -0.0737 0.0033 1.0000
8.750 1.2465 0.02024 0.01312 -0.0716 0.0031 1.0000
9.000 1.2563 0.02113 0.01410 -0.0690 0.0030 1.0000
9.250 1.2653 0.02209 0.01516 -0.0664 0.0029 1.0000
9.500 1.2745 0.02308 0.01624 -0.0642 0.0027 1.0000
9.750 1.2836 0.02413 0.01737 -0.0621 0.0025 1.0000
10.000 1.2933 0.02519 0.01851 -0.0602 0.0023 1.0000
10.250 1.3026 0.02634 0.01973 -0.0585 0.0021 1.0000
10.500 1.3126 0.02748 0.02094 -0.0570 0.0020 1.0000
10.750 1.3173 0.02913 0.02273 -0.0552 0.0019 1.0000
11.000 1.3211 0.03093 0.02464 -0.0535 0.0018 1.0000
11.250 1.3219 0.03313 0.02697 -0.0517 0.0017 1.0000
11.500 1.3208 0.03562 0.02960 -0.0501 0.0016 1.0000
11.750 1.3255 0.03762 0.03172 -0.0489 0.0016 1.0000
12.000 1.3295 0.03975 0.03398 -0.0479 0.0016 1.0000
12.250 1.3319 0.04213 0.03650 -0.0470 0.0015 1.0000
12.500 1.3340 0.04463 0.03913 -0.0462 0.0015 1.0000
12.750 1.3351 0.04731 0.04197 -0.0455 0.0015 1.0000
13.000 1.3367 0.05002 0.04482 -0.0451 0.0014 1.0000
13.250 1.3356 0.05312 0.04809 -0.0448 0.0014 1.0000
13.500 1.3341 0.05638 0.05150 -0.0447 0.0014 1.0000
13.750 1.3317 0.05990 0.05518 -0.0448 0.0013 1.0000
14.000 1.3276 0.06377 0.05923 -0.0452 0.0013 1.0000
14.250 1.3216 0.06812 0.06376 -0.0459 0.0013 1.0000
14.500 1.3145 0.07282 0.06864 -0.0470 0.0012 1.0000
14.750 1.3075 0.07769 0.07369 -0.0484 0.0012 1.0000
15.000 1.2972 0.08337 0.07956 -0.0504 0.0012 1.0000
15.250 1.2861 0.08945 0.08583 -0.0528 0.0012 1.0000
15.500 1.2753 0.09574 0.09230 -0.0555 0.0011 1.0000
15.750 1.2622 0.10281 0.09955 -0.0589 0.0011 1.0000
16.000 1.2488 0.11025 0.10717 -0.0628 0.0011 1.0000
16.250 1.2334 0.11845 0.11554 -0.0672 0.0011 1.0000
16.500 1.2174 0.12719 0.12446 -0.0722 0.0011 1.0000
16.750 1.2020 0.13621 0.13364 -0.0775 0.0011 1.0000
17.000 1.1857 0.14585 0.14343 -0.0833 0.0012 1.0000
17.250 1.1686 0.15626 0.15399 -0.0897 0.0012 1.0000
17.500 1.1513 0.16737 0.16523 -0.0964 0.0012 1.0000
17.750 1.1315 0.18010 0.17809 -0.1038 0.0013 1.0000
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Polar data table (+)
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