MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 50,000 Max Cl/Cd: 30.68 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh27-il-50000-n5.txt Download as CSV file: xf-mh27-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 27 11.99%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5087 0.10477 0.09794 -0.0397 1.0000 0.0342
-9.750 -0.5190 0.10001 0.09325 -0.0411 1.0000 0.0334
-9.500 -0.5340 0.09419 0.08749 -0.0436 1.0000 0.0326
-9.250 -0.5556 0.08856 0.08188 -0.0456 1.0000 0.0314
-9.000 -0.5866 0.08397 0.07724 -0.0445 1.0000 0.0306
-8.500 -0.6359 0.07913 0.07223 -0.0362 1.0000 0.0297
-8.250 -0.6510 0.07604 0.06907 -0.0325 1.0000 0.0296
-8.000 -0.6624 0.07307 0.06594 -0.0290 1.0000 0.0294
-7.750 -0.6729 0.07000 0.06275 -0.0253 1.0000 0.0292
-7.500 -0.6839 0.06664 0.05920 -0.0212 1.0000 0.0292
-7.250 -0.6892 0.06372 0.05610 -0.0177 1.0000 0.0289
-7.000 -0.6947 0.06047 0.05259 -0.0138 1.0000 0.0289
-6.750 -0.6969 0.05739 0.04922 -0.0100 1.0000 0.0288
-6.500 -0.6970 0.05428 0.04577 -0.0062 1.0000 0.0288
-6.250 -0.6939 0.05133 0.04247 -0.0027 1.0000 0.0287
-6.000 -0.6883 0.04843 0.03913 0.0008 1.0000 0.0289
-5.750 -0.6796 0.04573 0.03592 0.0041 1.0000 0.0293
-5.500 -0.6679 0.04333 0.03311 0.0070 1.0000 0.0299
-5.250 -0.6569 0.04090 0.03056 0.0090 1.0000 0.0328
-5.000 -0.6404 0.03896 0.02830 0.0111 1.0000 0.0342
-4.750 -0.6211 0.03700 0.02596 0.0130 1.0000 0.0368
-4.500 -0.5981 0.03503 0.02361 0.0145 1.0000 0.0385
-4.250 -0.5731 0.03336 0.02157 0.0157 1.0000 0.0406
-4.000 -0.5503 0.03183 0.01994 0.0166 1.0000 0.0462
-3.750 -0.5255 0.03059 0.01847 0.0176 1.0000 0.0553
-3.500 -0.5016 0.02947 0.01725 0.0184 1.0000 0.0686
-3.250 -0.4788 0.02813 0.01602 0.0193 1.0000 0.0982
-3.000 -0.3222 0.02749 0.01882 0.0002 1.0000 0.9327
-2.750 -0.1581 0.02897 0.01907 -0.0262 1.0000 1.0000
-2.500 -0.1485 0.02875 0.01863 -0.0238 1.0000 1.0000
-2.250 -0.1383 0.02858 0.01824 -0.0214 1.0000 1.0000
-2.000 -0.1278 0.02846 0.01790 -0.0190 1.0000 1.0000
-1.750 -0.1169 0.02838 0.01764 -0.0167 1.0000 1.0000
-1.500 -0.1058 0.02834 0.01744 -0.0144 1.0000 1.0000
-1.250 -0.0945 0.02834 0.01729 -0.0121 1.0000 1.0000
-1.000 -0.0831 0.02837 0.01719 -0.0098 1.0000 1.0000
-0.750 -0.0716 0.02844 0.01714 -0.0076 1.0000 1.0000
-0.500 -0.0600 0.02855 0.01710 -0.0054 1.0000 1.0000
-0.250 -0.0399 0.02873 0.01717 -0.0049 0.9976 1.0000
0.000 -0.0036 0.02908 0.01740 -0.0077 0.9899 1.0000
0.250 0.0326 0.02950 0.01772 -0.0105 0.9823 1.0000
0.500 0.0667 0.02980 0.01794 -0.0128 0.9737 1.0000
0.750 0.0997 0.03009 0.01818 -0.0148 0.9647 1.0000
1.000 0.1353 0.03046 0.01851 -0.0173 0.9564 1.0000
1.250 0.1677 0.03070 0.01874 -0.0190 0.9466 1.0000
1.500 0.1980 0.03089 0.01894 -0.0203 0.9361 1.0000
1.750 0.2301 0.03109 0.01916 -0.0219 0.9258 1.0000
2.000 0.2650 0.03127 0.01940 -0.0239 0.9158 1.0000
2.250 0.2988 0.03136 0.01956 -0.0256 0.9049 1.0000
2.500 0.3279 0.03137 0.01964 -0.0264 0.8924 1.0000
2.750 0.3572 0.03133 0.01968 -0.0270 0.8795 1.0000
3.000 0.3867 0.03123 0.01973 -0.0276 0.8660 1.0000
3.250 0.4164 0.03106 0.01969 -0.0281 0.8521 1.0000
3.500 0.4469 0.03081 0.01958 -0.0286 0.8379 1.0000
3.750 0.4675 0.03063 0.01952 -0.0272 0.8198 1.0000
4.000 0.4956 0.03031 0.01942 -0.0270 0.8032 1.0000
4.250 0.5272 0.02984 0.01914 -0.0272 0.7867 1.0000
4.500 0.5610 0.02921 0.01872 -0.0275 0.7704 1.0000
4.750 0.5836 0.02878 0.01849 -0.0259 0.7488 1.0000
5.000 0.6190 0.02794 0.01794 -0.0261 0.7289 1.0000
5.250 0.6477 0.02735 0.01756 -0.0251 0.7027 1.0000
5.500 0.6827 0.02664 0.01705 -0.0251 0.6714 1.0000
5.750 0.7231 0.02593 0.01650 -0.0259 0.6300 1.0000
6.000 0.7627 0.02555 0.01619 -0.0268 0.5757 1.0000
6.250 0.7888 0.02572 0.01625 -0.0256 0.5172 1.0000
6.500 0.8042 0.02621 0.01657 -0.0228 0.4618 1.0000
6.750 0.8125 0.02688 0.01706 -0.0191 0.4110 1.0000
7.000 0.8183 0.02764 0.01764 -0.0150 0.3648 1.0000
7.250 0.8222 0.02850 0.01834 -0.0109 0.3206 1.0000
7.500 0.8260 0.02944 0.01912 -0.0069 0.2800 1.0000
7.750 0.8291 0.03049 0.02001 -0.0029 0.2412 1.0000
8.000 0.8339 0.03159 0.02100 0.0006 0.2059 1.0000
8.250 0.8382 0.03282 0.02218 0.0041 0.1746 1.0000
8.500 0.8434 0.03412 0.02338 0.0073 0.1472 1.0000
8.750 0.8507 0.03552 0.02474 0.0102 0.1246 1.0000
9.000 0.8581 0.03701 0.02617 0.0130 0.1066 1.0000
9.250 0.8649 0.03846 0.02760 0.0158 0.0922 1.0000
9.500 0.8782 0.04013 0.02939 0.0179 0.0807 1.0000
9.750 0.8895 0.04181 0.03124 0.0201 0.0704 1.0000
10.000 0.8999 0.04357 0.03310 0.0223 0.0629 1.0000
10.250 0.9166 0.04571 0.03548 0.0238 0.0571 1.0000
10.500 0.9328 0.04829 0.03819 0.0252 0.0527 1.0000
10.750 0.9376 0.05061 0.04094 0.0280 0.0488 1.0000
11.000 0.9346 0.05247 0.04295 0.0314 0.0450 1.0000
11.250 0.9375 0.05488 0.04553 0.0337 0.0429 1.0000
11.500 0.9345 0.05817 0.04914 0.0368 0.0415 1.0000
11.750 0.9241 0.06127 0.05261 0.0401 0.0408 1.0000
12.000 0.9102 0.06457 0.05623 0.0432 0.0403 1.0000
12.250 0.8925 0.06817 0.06012 0.0459 0.0399 1.0000
12.500 0.8724 0.07204 0.06425 0.0478 0.0395 1.0000
12.750 0.8514 0.07634 0.06875 0.0487 0.0394 1.0000
13.000 0.8302 0.08114 0.07373 0.0487 0.0397 1.0000
13.250 0.8085 0.08645 0.07918 0.0475 0.0400 1.0000
13.500 0.7863 0.09255 0.08540 0.0453 0.0405 1.0000
13.750 0.7646 0.09934 0.09218 0.0422 0.0409 1.0000
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Polar data table (+)
Polar graphs
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