MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 115 11.06% (mh115-il) Reynolds number: 100,000 Max Cl/Cd: 64.91 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh115-il-100000-n5.txt Download as CSV file: xf-mh115-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1764 0.09154 0.08684 -0.0659 0.9612 0.0235
-7.500 -0.1677 0.08785 0.08316 -0.0688 0.9533 0.0226
-7.000 -0.1576 0.07791 0.07327 -0.0780 0.9352 0.0204
-6.750 -0.1387 0.07568 0.07105 -0.0808 0.9296 0.0223
-6.500 -0.1274 0.07115 0.06653 -0.0859 0.9202 0.0223
-6.250 -0.1138 0.06630 0.06167 -0.0920 0.9115 0.0229
-6.000 -0.0921 0.05948 0.05479 -0.1020 0.9044 0.0225
-5.750 -0.0720 0.05126 0.04641 -0.1125 0.8949 0.0221
-5.500 -0.0368 0.04055 0.03511 -0.1261 0.8893 0.0220
-5.250 -0.0008 0.03380 0.02754 -0.1337 0.8843 0.0221
-5.000 0.0306 0.02993 0.02301 -0.1369 0.8779 0.0228
-4.750 0.0702 0.02656 0.01890 -0.1404 0.8747 0.0244
-4.500 0.1089 0.02478 0.01680 -0.1431 0.8720 0.0277
-4.250 0.1343 0.02350 0.01518 -0.1429 0.8641 0.0314
-4.000 0.1694 0.02226 0.01378 -0.1445 0.8599 0.0363
-3.750 0.2072 0.02113 0.01249 -0.1465 0.8569 0.0451
-3.250 0.2672 0.01967 0.01089 -0.1475 0.8443 0.0688
-3.000 0.3025 0.01892 0.01013 -0.1490 0.8402 0.0874
-2.750 0.3292 0.01848 0.00969 -0.1489 0.8323 0.1108
-2.500 0.3644 0.01789 0.00916 -0.1504 0.8279 0.1494
-2.250 0.3930 0.01753 0.00891 -0.1507 0.8209 0.1964
-2.000 0.4238 0.01716 0.00866 -0.1513 0.8148 0.2553
-1.750 0.4590 0.01673 0.00834 -0.1527 0.8105 0.3258
-1.500 0.4833 0.01660 0.00836 -0.1521 0.8018 0.3910
-1.250 0.5164 0.01626 0.00816 -0.1529 0.7967 0.4708
-1.000 0.5414 0.01614 0.00818 -0.1521 0.7886 0.5451
-0.750 0.5704 0.01589 0.00807 -0.1519 0.7825 0.6253
-0.500 0.5934 0.01576 0.00807 -0.1504 0.7749 0.7024
-0.250 0.6151 0.01553 0.00795 -0.1485 0.7679 0.7856
0.000 0.6339 0.01525 0.00779 -0.1458 0.7603 0.9097
0.250 0.6664 0.01522 0.00760 -0.1466 0.7528 1.0000
0.500 0.6961 0.01532 0.00754 -0.1470 0.7452 1.0000
0.750 0.7259 0.01542 0.00749 -0.1473 0.7374 1.0000
1.000 0.7545 0.01554 0.00749 -0.1475 0.7293 1.0000
1.250 0.7841 0.01563 0.00746 -0.1477 0.7214 1.0000
1.500 0.8113 0.01580 0.00754 -0.1476 0.7127 1.0000
1.750 0.8414 0.01587 0.00751 -0.1479 0.7049 1.0000
2.000 0.8670 0.01607 0.00766 -0.1475 0.6954 1.0000
2.250 0.8978 0.01614 0.00762 -0.1479 0.6878 1.0000
2.500 0.9221 0.01636 0.00782 -0.1472 0.6774 1.0000
2.750 0.9494 0.01652 0.00792 -0.1471 0.6683 1.0000
3.000 0.9771 0.01666 0.00803 -0.1469 0.6589 1.0000
3.250 1.0018 0.01688 0.00823 -0.1463 0.6484 1.0000
3.500 1.0289 0.01704 0.00835 -0.1461 0.6387 1.0000
3.750 1.0550 0.01722 0.00850 -0.1457 0.6282 1.0000
4.000 1.0791 0.01745 0.00877 -0.1450 0.6168 1.0000
4.250 1.1045 0.01766 0.00897 -0.1445 0.6057 1.0000
4.500 1.1305 0.01785 0.00912 -0.1441 0.5947 1.0000
4.750 1.1543 0.01810 0.00941 -0.1433 0.5824 1.0000
5.000 1.1775 0.01837 0.00970 -0.1424 0.5696 1.0000
5.250 1.2009 0.01865 0.00999 -0.1416 0.5567 1.0000
5.500 1.2240 0.01893 0.01028 -0.1407 0.5435 1.0000
5.750 1.2467 0.01923 0.01061 -0.1398 0.5299 1.0000
6.000 1.2689 0.01955 0.01094 -0.1387 0.5157 1.0000
6.250 1.2903 0.01991 0.01131 -0.1376 0.5012 1.0000
6.500 1.3109 0.02029 0.01172 -0.1363 0.4861 1.0000
6.750 1.3308 0.02071 0.01215 -0.1350 0.4706 1.0000
7.000 1.3498 0.02116 0.01262 -0.1335 0.4547 1.0000
7.250 1.3678 0.02165 0.01314 -0.1319 0.4385 1.0000
7.500 1.3849 0.02218 0.01369 -0.1301 0.4219 1.0000
7.750 1.4008 0.02275 0.01427 -0.1282 0.4053 1.0000
8.000 1.4150 0.02336 0.01488 -0.1260 0.3889 1.0000
8.250 1.4280 0.02402 0.01557 -0.1237 0.3727 1.0000
8.500 1.4402 0.02474 0.01630 -0.1213 0.3568 1.0000
8.750 1.4516 0.02552 0.01710 -0.1189 0.3411 1.0000
9.000 1.4622 0.02636 0.01796 -0.1165 0.3257 1.0000
9.250 1.4723 0.02727 0.01890 -0.1141 0.3109 1.0000
9.500 1.4815 0.02825 0.01994 -0.1116 0.2963 1.0000
9.750 1.4901 0.02931 0.02104 -0.1093 0.2821 1.0000
10.000 1.4981 0.03045 0.02223 -0.1069 0.2683 1.0000
10.250 1.5051 0.03169 0.02352 -0.1046 0.2547 1.0000
10.500 1.5115 0.03303 0.02491 -0.1024 0.2416 1.0000
10.750 1.5172 0.03448 0.02641 -0.1002 0.2291 1.0000
11.000 1.5216 0.03606 0.02805 -0.0981 0.2169 1.0000
11.250 1.5259 0.03774 0.02980 -0.0961 0.2049 1.0000
11.500 1.5303 0.03949 0.03164 -0.0942 0.1934 1.0000
11.750 1.5335 0.04140 0.03364 -0.0925 0.1824 1.0000
12.000 1.5353 0.04350 0.03579 -0.0908 0.1722 1.0000
12.250 1.5364 0.04574 0.03810 -0.0893 0.1624 1.0000
12.500 1.5383 0.04801 0.04051 -0.0879 0.1525 1.0000
12.750 1.5383 0.05054 0.04311 -0.0867 0.1437 1.0000
13.000 1.5369 0.05328 0.04592 -0.0856 0.1352 1.0000
13.250 1.5368 0.05602 0.04880 -0.0847 0.1265 1.0000
13.500 1.5336 0.05918 0.05200 -0.0840 0.1193 1.0000
13.750 1.5317 0.06233 0.05530 -0.0835 0.1112 1.0000
14.000 1.5283 0.06576 0.05883 -0.0832 0.1043 1.0000
14.250 1.5240 0.06945 0.06263 -0.0831 0.0975 1.0000
14.500 1.5200 0.07323 0.06654 -0.0832 0.0911 1.0000
14.750 1.5139 0.07743 0.07084 -0.0836 0.0851 1.0000
15.000 1.5084 0.08167 0.07524 -0.0842 0.0794 1.0000
15.250 1.5012 0.08631 0.08001 -0.0851 0.0739 1.0000
15.500 1.4939 0.09111 0.08493 -0.0862 0.0691 1.0000
15.750 1.4863 0.09609 0.09007 -0.0875 0.0641 1.0000
16.000 1.4760 0.10160 0.09564 -0.0893 0.0604 1.0000
16.250 1.4691 0.10675 0.10101 -0.0910 0.0555 1.0000
16.500 1.4585 0.11262 0.10697 -0.0933 0.0521 1.0000
16.750 1.4501 0.11821 0.11271 -0.0956 0.0485 1.0000
17.000 1.4410 0.12405 0.11870 -0.0982 0.0450 1.0000
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Polar data table (+)
Polar graphs
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