MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 115 11.06% (mh115-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.37 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh115-il-1000000-n5.txt Download as CSV file: xf-mh115-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1985 0.02469 0.02196 -0.1574 0.8764 0.0033
-8.500 -0.1855 0.02068 0.01746 -0.1599 0.8639 0.0033
-8.250 -0.1659 0.01824 0.01464 -0.1609 0.8538 0.0033
-8.000 -0.1432 0.01660 0.01270 -0.1615 0.8441 0.0033
-7.750 -0.1191 0.01523 0.01106 -0.1618 0.8351 0.0033
-7.250 -0.0681 0.01328 0.00867 -0.1622 0.8176 0.0033
-7.000 -0.0418 0.01255 0.00775 -0.1623 0.8092 0.0033
-6.750 -0.0150 0.01187 0.00692 -0.1625 0.8006 0.0033
-6.500 0.0119 0.01132 0.00623 -0.1625 0.7925 0.0034
-6.250 0.0392 0.01082 0.00559 -0.1626 0.7842 0.0034
-6.000 0.0666 0.01040 0.00505 -0.1627 0.7765 0.0034
-5.750 0.0942 0.01003 0.00457 -0.1627 0.7683 0.0035
-5.500 0.1220 0.00969 0.00413 -0.1628 0.7610 0.0036
-5.250 0.1497 0.00939 0.00374 -0.1628 0.7530 0.0036
-5.000 0.1777 0.00906 0.00331 -0.1629 0.7459 0.0039
-4.750 0.2057 0.00882 0.00299 -0.1629 0.7381 0.0042
-4.500 0.2337 0.00863 0.00274 -0.1629 0.7311 0.0048
-4.250 0.2618 0.00847 0.00252 -0.1630 0.7234 0.0054
-4.000 0.2898 0.00831 0.00230 -0.1630 0.7161 0.0070
-3.750 0.3179 0.00815 0.00212 -0.1630 0.7084 0.0108
-3.500 0.3458 0.00803 0.00199 -0.1630 0.7010 0.0160
-3.250 0.3739 0.00794 0.00187 -0.1631 0.6930 0.0209
-3.000 0.4018 0.00784 0.00176 -0.1631 0.6857 0.0277
-2.750 0.4300 0.00771 0.00166 -0.1632 0.6778 0.0423
-2.500 0.4579 0.00759 0.00158 -0.1632 0.6703 0.0612
-2.250 0.4860 0.00751 0.00151 -0.1633 0.6622 0.0794
-2.000 0.5139 0.00745 0.00146 -0.1633 0.6547 0.0960
-1.750 0.5419 0.00738 0.00142 -0.1634 0.6464 0.1176
-1.250 0.5978 0.00728 0.00137 -0.1635 0.6302 0.1697
-1.000 0.6257 0.00722 0.00137 -0.1635 0.6223 0.2055
-0.750 0.6534 0.00719 0.00137 -0.1635 0.6135 0.2377
-0.500 0.6813 0.00716 0.00139 -0.1636 0.6052 0.2696
0.000 0.7366 0.00713 0.00144 -0.1636 0.5869 0.3398
0.250 0.7641 0.00713 0.00149 -0.1636 0.5778 0.3796
0.500 0.7915 0.00713 0.00155 -0.1635 0.5676 0.4201
0.750 0.8190 0.00714 0.00161 -0.1635 0.5579 0.4609
1.000 0.8461 0.00717 0.00168 -0.1634 0.5474 0.5038
1.250 0.8732 0.00721 0.00177 -0.1633 0.5363 0.5450
1.500 0.9003 0.00724 0.00186 -0.1632 0.5251 0.5889
1.750 0.9271 0.00730 0.00196 -0.1631 0.5134 0.6314
2.000 0.9535 0.00737 0.00208 -0.1629 0.5010 0.6757
2.250 0.9797 0.00745 0.00220 -0.1626 0.4883 0.7206
2.500 1.0055 0.00752 0.00234 -0.1622 0.4750 0.7692
2.750 1.0305 0.00759 0.00248 -0.1616 0.4613 0.8219
3.000 1.0521 0.00761 0.00262 -0.1602 0.4480 0.8925
3.250 1.0738 0.00765 0.00269 -0.1589 0.4338 1.0000
3.500 1.0993 0.00787 0.00284 -0.1585 0.4188 1.0000
3.750 1.1247 0.00809 0.00299 -0.1581 0.4043 1.0000
4.000 1.1497 0.00833 0.00316 -0.1577 0.3890 1.0000
4.250 1.1746 0.00858 0.00333 -0.1572 0.3740 1.0000
4.500 1.1992 0.00884 0.00353 -0.1567 0.3588 1.0000
4.750 1.2233 0.00912 0.00373 -0.1561 0.3424 1.0000
5.000 1.2471 0.00941 0.00394 -0.1554 0.3265 1.0000
5.250 1.2707 0.00972 0.00418 -0.1547 0.3104 1.0000
5.500 1.2937 0.01005 0.00442 -0.1540 0.2939 1.0000
5.750 1.3165 0.01037 0.00468 -0.1532 0.2783 1.0000
6.000 1.3397 0.01067 0.00493 -0.1524 0.2655 1.0000
6.250 1.3621 0.01100 0.00520 -0.1516 0.2515 1.0000
6.500 1.3842 0.01134 0.00548 -0.1506 0.2382 1.0000
6.750 1.4059 0.01168 0.00578 -0.1497 0.2259 1.0000
7.000 1.4267 0.01205 0.00610 -0.1485 0.2125 1.0000
7.250 1.4473 0.01242 0.00643 -0.1473 0.2011 1.0000
7.500 1.4662 0.01280 0.00677 -0.1458 0.1897 1.0000
7.750 1.4841 0.01321 0.00713 -0.1442 0.1773 1.0000
8.000 1.5020 0.01360 0.00749 -0.1425 0.1670 1.0000
8.250 1.5192 0.01403 0.00789 -0.1407 0.1568 1.0000
8.500 1.5351 0.01452 0.00834 -0.1388 0.1453 1.0000
8.750 1.5508 0.01503 0.00882 -0.1368 0.1348 1.0000
9.000 1.5655 0.01559 0.00934 -0.1348 0.1228 1.0000
9.250 1.5780 0.01629 0.00996 -0.1324 0.1087 1.0000
9.500 1.5894 0.01704 0.01065 -0.1300 0.0946 1.0000
9.750 1.6019 0.01777 0.01133 -0.1278 0.0843 1.0000
10.000 1.6136 0.01854 0.01207 -0.1255 0.0744 1.0000
10.250 1.6252 0.01934 0.01285 -0.1233 0.0656 1.0000
10.500 1.6361 0.02021 0.01369 -0.1211 0.0576 1.0000
10.750 1.6457 0.02118 0.01463 -0.1188 0.0497 1.0000
11.000 1.6545 0.02224 0.01567 -0.1165 0.0422 1.0000
11.250 1.6627 0.02338 0.01679 -0.1143 0.0350 1.0000
11.500 1.6691 0.02469 0.01808 -0.1119 0.0274 1.0000
11.750 1.6744 0.02613 0.01950 -0.1096 0.0205 1.0000
12.000 1.6805 0.02757 0.02095 -0.1075 0.0160 1.0000
12.250 1.6874 0.02900 0.02241 -0.1056 0.0130 1.0000
12.500 1.6940 0.03051 0.02395 -0.1038 0.0108 1.0000
12.750 1.7006 0.03207 0.02556 -0.1022 0.0089 1.0000
13.000 1.7069 0.03370 0.02725 -0.1006 0.0075 1.0000
13.250 1.7121 0.03549 0.02909 -0.0991 0.0063 1.0000
13.500 1.7181 0.03727 0.03093 -0.0978 0.0054 1.0000
13.750 1.7226 0.03927 0.03299 -0.0965 0.0047 1.0000
14.000 1.7281 0.04122 0.03501 -0.0954 0.0041 1.0000
14.250 1.7315 0.04344 0.03730 -0.0944 0.0034 1.0000
14.500 1.7348 0.04576 0.03969 -0.0935 0.0028 1.0000
14.750 1.7370 0.04828 0.04230 -0.0927 0.0023 1.0000
15.000 1.7386 0.05095 0.04504 -0.0920 0.0018 1.0000
15.250 1.7391 0.05383 0.04801 -0.0914 0.0014 1.0000
15.500 1.7390 0.05688 0.05115 -0.0911 0.0012 1.0000
15.750 1.7386 0.06007 0.05442 -0.0908 0.0010 1.0000
16.000 1.7378 0.06341 0.05786 -0.0908 0.0009 1.0000
16.250 1.7350 0.06711 0.06166 -0.0909 0.0007 1.0000
16.500 1.7312 0.07107 0.06573 -0.0912 0.0006 1.0000
16.750 1.7284 0.07499 0.06976 -0.0917 0.0006 1.0000
17.000 1.7249 0.07913 0.07400 -0.0923 0.0005 1.0000
17.250 1.7204 0.08348 0.07847 -0.0932 0.0005 1.0000
17.500 1.7151 0.08806 0.08317 -0.0942 0.0005 1.0000
17.750 1.7092 0.09287 0.08809 -0.0955 0.0005 1.0000
18.000 1.7020 0.09799 0.09333 -0.0970 0.0004 1.0000
18.250 1.6942 0.10328 0.09874 -0.0988 0.0004 1.0000
18.500 1.6863 0.10868 0.10426 -0.1007 0.0004 1.0000
18.750 1.6771 0.11438 0.11008 -0.1029 0.0004 1.0000
19.000 1.6682 0.12011 0.11594 -0.1053 0.0004 1.0000
19.250 1.6586 0.12604 0.12199 -0.1079 0.0003 1.0000
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Polar data table (+)
Polar graphs
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