MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 114 13.02% (mh114-il) Reynolds number: 100,000 Max Cl/Cd: 56.17 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh114-il-100000.txt Download as CSV file: xf-mh114-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 114 13.02%
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.1785 0.11174 0.10749 -0.0617 0.9413 0.0817
-7.000 -0.1963 0.11154 0.10736 -0.0657 0.9328 0.0831
-6.750 -0.2092 0.11023 0.10611 -0.0710 0.9228 0.0835
-6.500 -0.1587 0.10316 0.09898 -0.0656 0.9236 0.0880
-6.250 -0.1556 0.10121 0.09705 -0.0658 0.9171 0.0917
-6.000 -0.1622 0.09960 0.09548 -0.0664 0.9085 0.0943
-5.750 -0.1766 0.09804 0.09397 -0.0745 0.8967 0.0969
-5.500 -0.1618 0.09365 0.08960 -0.0734 0.8927 0.0992
-5.250 -0.1342 0.09057 0.08649 -0.0734 0.8899 0.1055
-5.000 -0.1445 0.08898 0.08494 -0.0741 0.8789 0.1094
-4.750 -0.1187 0.08354 0.07948 -0.0835 0.8743 0.1149
-4.500 -0.1249 0.08241 0.07839 -0.0793 0.8649 0.1171
-4.250 -0.0856 0.07612 0.07193 -0.0952 0.8595 0.1293
-4.000 -0.0587 0.07337 0.06887 -0.1055 0.8503 0.1438
-3.750 -0.0475 0.06979 0.06549 -0.1017 0.8458 0.1456
-3.500 0.0645 0.04920 0.04330 -0.1331 0.8458 0.0722
-3.250 0.1232 0.04384 0.03734 -0.1406 0.8438 0.0650
-3.000 0.1838 0.04020 0.03288 -0.1473 0.8420 0.0677
-2.750 0.2018 0.03913 0.03139 -0.1465 0.8327 0.0687
-2.500 0.2482 0.03710 0.02898 -0.1498 0.8291 0.0755
-2.250 0.2979 0.03539 0.02706 -0.1532 0.8266 0.0882
-2.000 0.3132 0.03529 0.02688 -0.1516 0.8171 0.1002
-1.750 0.3557 0.03418 0.02584 -0.1540 0.8130 0.1318
-1.500 0.4053 0.03289 0.02483 -0.1575 0.8106 0.2014
-1.250 0.4181 0.03314 0.02536 -0.1558 0.8003 0.2666
-1.000 0.4614 0.03230 0.02501 -0.1583 0.7965 0.4070
-0.750 0.5065 0.03155 0.02460 -0.1603 0.7941 0.5402
-0.500 0.5120 0.03234 0.02558 -0.1570 0.7825 0.6055
-0.250 0.5482 0.03164 0.02508 -0.1568 0.7793 0.7113
0.000 0.5499 0.03225 0.02588 -0.1522 0.7685 0.7859
0.250 0.5754 0.03129 0.02502 -0.1501 0.7641 1.0000
0.500 0.6292 0.03070 0.02407 -0.1542 0.7621 1.0000
0.750 0.6389 0.03189 0.02512 -0.1524 0.7497 1.0000
1.000 0.6876 0.03122 0.02420 -0.1551 0.7472 1.0000
1.250 0.7393 0.03032 0.02310 -0.1582 0.7458 1.0000
1.500 0.7444 0.03166 0.02436 -0.1555 0.7326 1.0000
1.750 0.7950 0.03067 0.02321 -0.1582 0.7309 1.0000
2.000 0.8474 0.02967 0.02206 -0.1613 0.7292 1.0000
2.500 0.8853 0.03075 0.02302 -0.1588 0.7105 1.0000
2.750 0.9095 0.03099 0.02320 -0.1582 0.7019 1.0000
3.000 0.9630 0.02980 0.02193 -0.1613 0.6999 1.0000
3.250 1.0201 0.02855 0.02060 -0.1652 0.6981 1.0000
3.500 1.0231 0.02968 0.02173 -0.1615 0.6854 1.0000
3.750 1.0797 0.02840 0.02038 -0.1653 0.6830 1.0000
4.000 1.0872 0.02934 0.02133 -0.1622 0.6712 1.0000
4.250 1.1415 0.02813 0.02008 -0.1657 0.6679 1.0000
4.500 1.1547 0.02881 0.02077 -0.1634 0.6570 1.0000
4.750 1.2054 0.02776 0.01968 -0.1663 0.6524 1.0000
5.000 1.2227 0.02823 0.02019 -0.1646 0.6421 1.0000
5.250 1.2709 0.02733 0.01925 -0.1672 0.6363 1.0000
5.500 1.2874 0.02782 0.01978 -0.1654 0.6256 1.0000
5.750 1.3378 0.02690 0.01881 -0.1684 0.6194 1.0000
6.000 1.3506 0.02751 0.01949 -0.1660 0.6080 1.0000
6.250 1.3922 0.02702 0.01895 -0.1678 0.6001 1.0000
6.500 1.4153 0.02721 0.01919 -0.1668 0.5894 1.0000
6.750 1.4350 0.02758 0.01961 -0.1654 0.5786 1.0000
7.000 1.4807 0.02702 0.01897 -0.1679 0.5699 1.0000
7.250 1.4932 0.02761 0.01965 -0.1654 0.5580 1.0000
7.500 1.5129 0.02800 0.02009 -0.1640 0.5468 1.0000
7.750 1.5471 0.02791 0.01996 -0.1648 0.5365 1.0000
8.000 1.5685 0.02822 0.02031 -0.1636 0.5249 1.0000
8.250 1.5823 0.02882 0.02100 -0.1613 0.5131 1.0000
8.500 1.6058 0.02913 0.02132 -0.1606 0.5017 1.0000
8.750 1.6389 0.02918 0.02131 -0.1612 0.4904 1.0000
9.000 1.6472 0.02991 0.02215 -0.1581 0.4783 1.0000
9.250 1.6598 0.03058 0.02289 -0.1557 0.4666 1.0000
9.500 1.6808 0.03100 0.02334 -0.1546 0.4549 1.0000
9.750 1.7084 0.03128 0.02356 -0.1545 0.4428 1.0000
10.000 1.7075 0.03220 0.02462 -0.1500 0.4314 1.0000
10.250 1.7161 0.03299 0.02548 -0.1471 0.4200 1.0000
10.500 1.7334 0.03356 0.02606 -0.1456 0.4081 1.0000
10.750 1.7545 0.03403 0.02648 -0.1446 0.3958 1.0000
11.000 1.7470 0.03532 0.02795 -0.1396 0.3850 1.0000
11.250 1.7534 0.03631 0.02900 -0.1367 0.3736 1.0000
11.500 1.7668 0.03708 0.02976 -0.1348 0.3618 1.0000
11.750 1.7743 0.03804 0.03077 -0.1322 0.3500 1.0000
12.000 1.7686 0.03964 0.03252 -0.1282 0.3392 1.0000
12.250 1.7734 0.04089 0.03381 -0.1256 0.3280 1.0000
12.500 1.7838 0.04191 0.03480 -0.1237 0.3162 1.0000
12.750 1.7790 0.04368 0.03670 -0.1203 0.3053 1.0000
13.000 1.7755 0.04558 0.03872 -0.1174 0.2947 1.0000
13.250 1.7797 0.04710 0.04026 -0.1152 0.2836 1.0000
13.500 1.7850 0.04857 0.04170 -0.1133 0.2723 1.0000
13.750 1.7725 0.05132 0.04466 -0.1102 0.2625 1.0000
14.000 1.7721 0.05339 0.04678 -0.1082 0.2521 1.0000
14.250 1.7780 0.05502 0.04834 -0.1066 0.2411 1.0000
14.500 1.7639 0.05829 0.05185 -0.1042 0.2321 1.0000
14.750 1.7613 0.06083 0.05444 -0.1026 0.2224 1.0000
15.000 1.7662 0.06272 0.05625 -0.1014 0.2119 1.0000
15.250 1.7503 0.06667 0.06047 -0.0997 0.2036 1.0000
15.500 1.7484 0.06943 0.06326 -0.0986 0.1945 1.0000
15.750 1.7470 0.07212 0.06595 -0.0977 0.1852 1.0000
16.000 1.7342 0.07635 0.07039 -0.0969 0.1775 1.0000
16.250 1.7369 0.07878 0.07275 -0.0962 0.1684 1.0000
16.500 1.7223 0.08341 0.07761 -0.0959 0.1614 1.0000
16.750 1.7209 0.08652 0.08074 -0.0956 0.1534 1.0000
17.000 1.7120 0.09064 0.08497 -0.0956 0.1462 1.0000
17.250 1.7060 0.09453 0.08896 -0.0957 0.1392 1.0000
17.500 1.7011 0.09821 0.09269 -0.0960 0.1321 1.0000
17.750 1.6921 0.10272 0.09734 -0.0967 0.1261 1.0000
18.000 1.6867 0.10663 0.10133 -0.0974 0.1196 1.0000
18.250 1.6794 0.11101 0.10583 -0.0983 0.1139 1.0000
18.500 1.6685 0.11601 0.11099 -0.0998 0.1087 1.0000
18.750 1.6692 0.11911 0.11408 -0.1005 0.1026 1.0000
19.000 1.6511 0.12557 0.12081 -0.1030 0.0988 1.0000
19.250 1.6622 0.12680 0.12186 -0.1030 0.0919 1.0000
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Polar data table (+)
Polar graphs
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