MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 115 11.06% (mh115-il) Reynolds number: 100,000 Max Cl/Cd: 61.9 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh115-il-100000.txt Download as CSV file: xf-mh115-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3407 0.12414 0.11993 -0.0292 1.0000 0.0676
-8.250 -0.3583 0.12390 0.11978 -0.0280 1.0000 0.0677
-8.000 -0.3753 0.12343 0.11941 -0.0265 1.0000 0.0678
-7.750 -0.3398 0.11519 0.11113 -0.0227 1.0000 0.0702
-7.500 -0.3435 0.11351 0.10950 -0.0207 1.0000 0.0714
-7.250 -0.3338 0.11062 0.10663 -0.0226 0.9969 0.0738
-7.000 -0.3198 0.10730 0.10331 -0.0276 0.9909 0.0770
-6.750 -0.3230 0.10575 0.10181 -0.0352 0.9812 0.0799
-6.500 -0.3117 0.10154 0.09764 -0.0493 0.9706 0.0810
-6.250 -0.2929 0.09718 0.09327 -0.0410 0.9687 0.0834
-6.000 -0.2745 0.09390 0.08998 -0.0431 0.9623 0.0872
-5.750 -0.2626 0.09047 0.08655 -0.0509 0.9524 0.0927
-5.500 -0.2404 0.08520 0.08128 -0.0585 0.9463 0.0972
-5.250 -0.2305 0.08293 0.07903 -0.0572 0.9380 0.1016
-5.000 -0.1982 0.07637 0.07235 -0.0754 0.9291 0.1104
-4.750 -0.1899 0.07462 0.07067 -0.0696 0.9225 0.1142
-4.500 -0.1472 0.06839 0.06428 -0.0837 0.9174 0.1266
-4.250 -0.1394 0.06644 0.06235 -0.0814 0.9085 0.1300
-4.000 -0.0969 0.06112 0.05688 -0.0916 0.9037 0.1434
-3.750 -0.0177 0.04820 0.04317 -0.1127 0.9020 0.1001
-3.500 0.0583 0.03575 0.02891 -0.1262 0.9007 0.0614
-3.250 0.0924 0.03352 0.02602 -0.1280 0.8937 0.0659
-3.000 0.1375 0.03119 0.02331 -0.1314 0.8900 0.0746
-2.750 0.1865 0.02946 0.02120 -0.1349 0.8872 0.0922
-2.500 0.2088 0.02882 0.02044 -0.1342 0.8782 0.1077
-2.250 0.2516 0.02763 0.01927 -0.1368 0.8742 0.1365
-2.000 0.2846 0.02690 0.01867 -0.1379 0.8680 0.1755
-1.750 0.3177 0.02628 0.01830 -0.1391 0.8614 0.2394
-1.500 0.3623 0.02535 0.01782 -0.1420 0.8578 0.3553
-1.250 0.3837 0.02526 0.01809 -0.1412 0.8488 0.4589
-1.000 0.4206 0.02463 0.01791 -0.1420 0.8441 0.6061
-0.750 0.4404 0.02441 0.01805 -0.1396 0.8369 0.7365
-0.500 0.4581 0.02378 0.01769 -0.1362 0.8295 1.0000
-0.250 0.5105 0.02342 0.01695 -0.1404 0.8267 1.0000
0.000 0.5296 0.02400 0.01734 -0.1394 0.8157 1.0000
0.250 0.5787 0.02356 0.01666 -0.1427 0.8126 1.0000
0.500 0.6000 0.02405 0.01700 -0.1419 0.8024 1.0000
0.750 0.6464 0.02365 0.01643 -0.1446 0.7984 1.0000
1.000 0.6902 0.02328 0.01591 -0.1469 0.7943 1.0000
1.250 0.7134 0.02362 0.01617 -0.1462 0.7842 1.0000
1.500 0.7614 0.02299 0.01542 -0.1489 0.7810 1.0000
1.750 0.7806 0.02348 0.01586 -0.1475 0.7698 1.0000
2.000 0.8271 0.02283 0.01512 -0.1499 0.7660 1.0000
2.250 0.8479 0.02324 0.01551 -0.1488 0.7550 1.0000
2.500 0.8934 0.02258 0.01477 -0.1510 0.7506 1.0000
2.750 0.9146 0.02295 0.01513 -0.1498 0.7393 1.0000
3.000 0.9604 0.02224 0.01436 -0.1519 0.7346 1.0000
3.250 0.9811 0.02260 0.01475 -0.1506 0.7228 1.0000
3.500 1.0111 0.02257 0.01470 -0.1506 0.7135 1.0000
3.750 1.0480 0.02220 0.01429 -0.1515 0.7054 1.0000
4.000 1.0720 0.02240 0.01454 -0.1506 0.6939 1.0000
4.250 1.1053 0.02220 0.01432 -0.1510 0.6846 1.0000
4.500 1.1379 0.02201 0.01412 -0.1512 0.6744 1.0000
4.750 1.1618 0.02218 0.01434 -0.1503 0.6619 1.0000
5.000 1.1890 0.02222 0.01440 -0.1497 0.6500 1.0000
5.250 1.2201 0.02210 0.01428 -0.1498 0.6387 1.0000
5.500 1.2523 0.02194 0.01411 -0.1500 0.6269 1.0000
5.750 1.2761 0.02209 0.01430 -0.1489 0.6129 1.0000
6.000 1.3005 0.02222 0.01446 -0.1480 0.5987 1.0000
6.250 1.3251 0.02235 0.01464 -0.1471 0.5841 1.0000
6.500 1.3496 0.02249 0.01480 -0.1462 0.5690 1.0000
6.750 1.3739 0.02264 0.01497 -0.1452 0.5534 1.0000
7.000 1.3978 0.02282 0.01514 -0.1442 0.5373 1.0000
7.250 1.4214 0.02302 0.01536 -0.1431 0.5207 1.0000
7.500 1.4429 0.02331 0.01564 -0.1418 0.5033 1.0000
7.750 1.4604 0.02373 0.01612 -0.1398 0.4849 1.0000
8.000 1.4785 0.02416 0.01659 -0.1380 0.4664 1.0000
8.250 1.4968 0.02461 0.01704 -0.1362 0.4479 1.0000
8.500 1.5153 0.02511 0.01750 -0.1345 0.4295 1.0000
8.750 1.5311 0.02573 0.01812 -0.1324 0.4111 1.0000
9.000 1.5438 0.02645 0.01890 -0.1299 0.3923 1.0000
9.250 1.5564 0.02720 0.01966 -0.1275 0.3739 1.0000
9.500 1.5685 0.02800 0.02046 -0.1250 0.3560 1.0000
9.750 1.5795 0.02886 0.02129 -0.1224 0.3385 1.0000
10.000 1.5888 0.02980 0.02217 -0.1196 0.3215 1.0000
10.250 1.5938 0.03083 0.02327 -0.1161 0.3051 1.0000
10.500 1.5981 0.03196 0.02443 -0.1128 0.2890 1.0000
10.750 1.6022 0.03319 0.02568 -0.1096 0.2733 1.0000
11.000 1.6057 0.03452 0.02704 -0.1065 0.2581 1.0000
11.250 1.6089 0.03596 0.02850 -0.1036 0.2434 1.0000
11.500 1.6121 0.03751 0.03006 -0.1008 0.2294 1.0000
11.750 1.6151 0.03915 0.03170 -0.0982 0.2159 1.0000
12.000 1.6185 0.04087 0.03340 -0.0958 0.2030 1.0000
12.250 1.6171 0.04279 0.03545 -0.0931 0.1913 1.0000
12.500 1.6158 0.04487 0.03764 -0.0907 0.1800 1.0000
12.750 1.6154 0.04703 0.03987 -0.0885 0.1694 1.0000
13.000 1.6158 0.04920 0.04204 -0.0867 0.1591 1.0000
13.250 1.6124 0.05163 0.04456 -0.0848 0.1495 1.0000
13.500 1.6078 0.05439 0.04748 -0.0831 0.1404 1.0000
13.750 1.6055 0.05706 0.05016 -0.0817 0.1314 1.0000
14.000 1.5992 0.06007 0.05329 -0.0804 0.1230 1.0000
14.250 1.5921 0.06347 0.05686 -0.0794 0.1148 1.0000
14.500 1.5881 0.06663 0.05998 -0.0786 0.1064 1.0000
14.750 1.5775 0.07063 0.06420 -0.0781 0.0991 1.0000
15.000 1.5699 0.07459 0.06825 -0.0778 0.0915 1.0000
15.250 1.5669 0.07807 0.07158 -0.0775 0.0830 1.0000
15.500 1.5519 0.08330 0.07719 -0.0780 0.0777 1.0000
15.750 1.5480 0.08714 0.08094 -0.0781 0.0707 1.0000
16.000 1.5349 0.09253 0.08664 -0.0791 0.0660 1.0000
16.250 1.5330 0.09627 0.09027 -0.0794 0.0600 1.0000
16.500 1.5190 0.10211 0.09646 -0.0811 0.0567 1.0000
16.750 1.5174 0.10582 0.10009 -0.0820 0.0520 1.0000
17.000 1.5074 0.11136 0.10588 -0.0836 0.0492 1.0000
17.250 1.4944 0.11747 0.11227 -0.0862 0.0469 1.0000
17.500 1.4917 0.12157 0.11637 -0.0878 0.0436 1.0000
17.750 1.4855 0.12670 0.12162 -0.0897 0.0414 1.0000
18.000 1.4693 0.13389 0.12913 -0.0936 0.0404 1.0000
18.250 1.4538 0.14123 0.13674 -0.0979 0.0395 1.0000
18.500 1.4371 0.14911 0.14488 -0.1027 0.0391 1.0000
18.750 1.4168 0.15818 0.15421 -0.1087 0.0392 1.0000
19.000 1.3929 0.16869 0.16495 -0.1160 0.0402 1.0000
19.250 1.3689 0.17984 0.17627 -0.1238 0.0413 1.0000
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Polar data table (+)
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