MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 115 11.06% (mh115-il) Reynolds number: 500,000 Max Cl/Cd: 130.69 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh115-il-500000.txt Download as CSV file: xf-mh115-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1712 0.10211 0.09984 -0.0693 0.9851 0.0164
-9.250 -0.1576 0.09753 0.09527 -0.0742 0.9825 0.0165
-9.000 -0.1467 0.09350 0.09125 -0.0763 0.9785 0.0167
-8.750 -0.1286 0.09066 0.08841 -0.0785 0.9760 0.0170
-8.500 -0.1103 0.08724 0.08499 -0.0821 0.9739 0.0174
-8.250 -0.0911 0.08359 0.08133 -0.0866 0.9721 0.0179
-8.000 -0.0803 0.08025 0.07800 -0.0892 0.9647 0.0184
-7.750 -0.0628 0.07592 0.07367 -0.0946 0.9614 0.0192
-7.500 -0.0517 0.06977 0.06754 -0.1028 0.9528 0.0204
-7.250 -0.0296 0.06284 0.06060 -0.1138 0.9471 0.0205
-7.000 -0.0141 0.05823 0.05599 -0.1194 0.9392 0.0209
-6.750 0.0127 0.05492 0.05265 -0.1254 0.9338 0.0214
-6.500 0.0362 0.05052 0.04821 -0.1331 0.9235 0.0219
-6.250 0.0623 0.04404 0.04161 -0.1442 0.9122 0.0228
-6.000 0.0694 0.01706 0.01227 -0.1633 0.8920 0.0104
-5.750 0.0991 0.01572 0.01061 -0.1641 0.8853 0.0102
-5.500 0.1253 0.01424 0.00885 -0.1641 0.8767 0.0102
-5.250 0.1540 0.01286 0.00725 -0.1646 0.8699 0.0104
-5.000 0.1809 0.01200 0.00628 -0.1646 0.8614 0.0108
-4.750 0.2098 0.01141 0.00560 -0.1649 0.8544 0.0116
-4.500 0.2376 0.01093 0.00499 -0.1648 0.8461 0.0130
-4.250 0.2665 0.01041 0.00439 -0.1651 0.8388 0.0155
-4.000 0.2946 0.00993 0.00387 -0.1651 0.8307 0.0215
-3.750 0.3232 0.00962 0.00355 -0.1653 0.8234 0.0336
-3.500 0.3510 0.00944 0.00336 -0.1653 0.8152 0.0450
-3.250 0.3794 0.00921 0.00312 -0.1654 0.8077 0.0589
-3.000 0.4074 0.00897 0.00290 -0.1654 0.7996 0.0800
-2.750 0.4358 0.00875 0.00272 -0.1656 0.7921 0.1114
-2.500 0.4637 0.00855 0.00260 -0.1657 0.7840 0.1482
-2.250 0.4919 0.00840 0.00250 -0.1658 0.7765 0.1892
-2.000 0.5198 0.00826 0.00243 -0.1658 0.7685 0.2347
-1.750 0.5479 0.00812 0.00239 -0.1659 0.7609 0.2862
-1.500 0.5757 0.00799 0.00236 -0.1660 0.7529 0.3464
-1.250 0.6037 0.00787 0.00236 -0.1660 0.7453 0.4061
-1.000 0.6314 0.00777 0.00237 -0.1660 0.7374 0.4671
-0.750 0.6591 0.00769 0.00240 -0.1660 0.7298 0.5273
-0.500 0.6865 0.00762 0.00243 -0.1659 0.7218 0.5880
-0.250 0.7136 0.00756 0.00248 -0.1657 0.7140 0.6486
0.000 0.7401 0.00750 0.00253 -0.1653 0.7061 0.7078
0.250 0.7658 0.00745 0.00260 -0.1647 0.6981 0.7673
0.500 0.7894 0.00739 0.00264 -0.1635 0.6901 0.8299
0.750 0.8075 0.00726 0.00266 -0.1610 0.6822 0.9112
1.000 0.8351 0.00725 0.00260 -0.1608 0.6740 1.0000
1.250 0.8628 0.00733 0.00264 -0.1608 0.6653 1.0000
1.500 0.8903 0.00747 0.00267 -0.1607 0.6570 1.0000
1.750 0.9175 0.00756 0.00274 -0.1606 0.6478 1.0000
2.000 0.9446 0.00768 0.00279 -0.1605 0.6392 1.0000
2.250 0.9715 0.00780 0.00286 -0.1603 0.6296 1.0000
2.500 0.9982 0.00792 0.00294 -0.1601 0.6200 1.0000
2.750 1.0246 0.00808 0.00303 -0.1598 0.6106 1.0000
3.000 1.0510 0.00820 0.00313 -0.1595 0.6001 1.0000
3.250 1.0771 0.00834 0.00323 -0.1592 0.5898 1.0000
3.500 1.1028 0.00851 0.00336 -0.1588 0.5791 1.0000
3.750 1.1283 0.00867 0.00348 -0.1583 0.5675 1.0000
4.000 1.1538 0.00883 0.00362 -0.1579 0.5556 1.0000
4.250 1.1788 0.00902 0.00377 -0.1574 0.5433 1.0000
4.500 1.2034 0.00922 0.00394 -0.1568 0.5304 1.0000
4.750 1.2276 0.00944 0.00411 -0.1561 0.5168 1.0000
5.000 1.2514 0.00968 0.00430 -0.1554 0.5023 1.0000
5.250 1.2748 0.00993 0.00452 -0.1546 0.4870 1.0000
5.500 1.2978 0.01020 0.00474 -0.1538 0.4707 1.0000
5.750 1.3203 0.01050 0.00499 -0.1529 0.4538 1.0000
6.000 1.3423 0.01081 0.00526 -0.1519 0.4363 1.0000
6.250 1.3635 0.01116 0.00555 -0.1507 0.4183 1.0000
6.500 1.3842 0.01154 0.00586 -0.1495 0.4008 1.0000
6.750 1.4046 0.01192 0.00620 -0.1483 0.3842 1.0000
7.250 1.4436 0.01275 0.00693 -0.1455 0.3508 1.0000
7.500 1.4617 0.01316 0.00731 -0.1438 0.3348 1.0000
7.750 1.4786 0.01361 0.00772 -0.1420 0.3186 1.0000
8.000 1.4951 0.01407 0.00815 -0.1401 0.3034 1.0000
8.250 1.5111 0.01457 0.00861 -0.1381 0.2884 1.0000
8.500 1.5263 0.01510 0.00911 -0.1361 0.2730 1.0000
8.750 1.5413 0.01566 0.00965 -0.1340 0.2582 1.0000
9.000 1.5555 0.01627 0.01022 -0.1319 0.2438 1.0000
9.250 1.5691 0.01692 0.01084 -0.1298 0.2291 1.0000
9.500 1.5819 0.01761 0.01151 -0.1276 0.2148 1.0000
9.750 1.5940 0.01838 0.01224 -0.1253 0.2000 1.0000
10.000 1.6047 0.01924 0.01306 -0.1230 0.1834 1.0000
10.250 1.6142 0.02019 0.01395 -0.1206 0.1669 1.0000
10.500 1.6232 0.02121 0.01492 -0.1182 0.1520 1.0000
10.750 1.6324 0.02226 0.01594 -0.1159 0.1393 1.0000
11.000 1.6411 0.02337 0.01704 -0.1137 0.1277 1.0000
11.250 1.6491 0.02457 0.01823 -0.1115 0.1171 1.0000
11.500 1.6557 0.02591 0.01956 -0.1093 0.1073 1.0000
11.750 1.6637 0.02720 0.02087 -0.1074 0.0981 1.0000
12.000 1.6707 0.02862 0.02230 -0.1055 0.0894 1.0000
12.250 1.6760 0.03021 0.02389 -0.1035 0.0812 1.0000
12.500 1.6807 0.03192 0.02559 -0.1017 0.0729 1.0000
12.750 1.6860 0.03364 0.02733 -0.1000 0.0648 1.0000
13.000 1.6895 0.03557 0.02927 -0.0984 0.0568 1.0000
13.250 1.6914 0.03773 0.03142 -0.0968 0.0490 1.0000
13.500 1.6922 0.04008 0.03377 -0.0954 0.0419 1.0000
13.750 1.6928 0.04254 0.03625 -0.0941 0.0352 1.0000
14.000 1.6922 0.04522 0.03896 -0.0929 0.0294 1.0000
14.250 1.6905 0.04814 0.04192 -0.0919 0.0243 1.0000
14.500 1.6877 0.05129 0.04513 -0.0910 0.0202 1.0000
14.750 1.6840 0.05468 0.04857 -0.0904 0.0172 1.0000
15.000 1.6800 0.05825 0.05221 -0.0900 0.0148 1.0000
15.250 1.6764 0.06189 0.05597 -0.0897 0.0129 1.0000
15.500 1.6700 0.06602 0.06018 -0.0897 0.0114 1.0000
15.750 1.6653 0.07005 0.06434 -0.0899 0.0099 1.0000
16.000 1.6567 0.07482 0.06920 -0.0905 0.0088 1.0000
16.250 1.6495 0.07953 0.07405 -0.0912 0.0076 1.0000
16.500 1.6394 0.08480 0.07943 -0.0923 0.0067 1.0000
16.750 1.6272 0.09065 0.08542 -0.0937 0.0060 1.0000
17.000 1.6183 0.09606 0.09098 -0.0952 0.0054 1.0000
17.250 1.6062 0.10216 0.09720 -0.0972 0.0050 1.0000
17.500 1.5889 0.10937 0.10456 -0.0999 0.0047 1.0000
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Polar data table (+)
Polar graphs
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