MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 50,000 Max Cl/Cd: 37.95 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh122-il-50000-n5.txt Download as CSV file: xf-mh122-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 122 9.32%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4398 0.09734 0.09089 -0.0358 1.0000 0.0440
-7.500 -0.4492 0.09480 0.08845 -0.0341 1.0000 0.0426
-7.250 -0.4608 0.09245 0.08620 -0.0326 1.0000 0.0415
-7.000 -0.4704 0.08953 0.08337 -0.0323 1.0000 0.0403
-6.750 -0.4778 0.08590 0.07980 -0.0333 1.0000 0.0390
-6.500 -0.4836 0.08089 0.07494 -0.0367 1.0000 0.0374
-6.250 -0.4844 0.07395 0.06766 -0.0454 1.0000 0.0338
-6.000 -0.4814 0.06994 0.06365 -0.0455 1.0000 0.0331
-5.750 -0.4756 0.06578 0.05940 -0.0467 1.0000 0.0326
-5.500 -0.4664 0.06148 0.05483 -0.0485 1.0000 0.0319
-5.250 -0.4527 0.05705 0.05015 -0.0508 1.0000 0.0313
-5.000 -0.4345 0.05262 0.04536 -0.0534 1.0000 0.0306
-4.750 -0.4117 0.04820 0.04048 -0.0560 1.0000 0.0301
-4.500 -0.3855 0.04418 0.03593 -0.0583 1.0000 0.0298
-4.250 -0.3575 0.04065 0.03184 -0.0600 1.0000 0.0298
-4.000 -0.3287 0.03758 0.02819 -0.0612 1.0000 0.0301
-3.750 -0.3000 0.03498 0.02504 -0.0617 1.0000 0.0309
-3.500 -0.2691 0.03298 0.02249 -0.0623 0.9988 0.0329
-3.250 -0.2386 0.03116 0.02048 -0.0633 0.9967 0.0389
-3.000 -0.2080 0.02982 0.01883 -0.0635 0.9947 0.0443
-2.750 -0.1788 0.02846 0.01728 -0.0636 0.9926 0.0495
-2.500 -0.1470 0.02731 0.01586 -0.0648 0.9902 0.0726
-2.250 -0.1072 0.02501 0.01417 -0.0684 0.9893 0.1747
-2.000 -0.0823 0.02394 0.01477 -0.0677 0.9872 0.5844
-1.750 -0.0666 0.02419 0.01528 -0.0638 0.9836 0.6991
-1.500 -0.0512 0.02422 0.01530 -0.0602 0.9795 0.7608
-1.250 -0.0270 0.02420 0.01507 -0.0596 0.9755 0.7925
-1.000 -0.0005 0.02422 0.01491 -0.0594 0.9717 0.8241
-0.750 0.0250 0.02416 0.01466 -0.0592 0.9676 0.8658
-0.500 0.0577 0.02386 0.01425 -0.0609 0.9615 0.9871
-0.250 0.0972 0.02431 0.01433 -0.0646 0.9582 1.0000
0.000 0.1294 0.02465 0.01438 -0.0666 0.9534 1.0000
0.250 0.1629 0.02507 0.01450 -0.0687 0.9488 1.0000
0.500 0.1995 0.02559 0.01480 -0.0713 0.9449 1.0000
0.750 0.2271 0.02594 0.01500 -0.0722 0.9389 1.0000
1.000 0.2607 0.02643 0.01535 -0.0741 0.9340 1.0000
1.250 0.2913 0.02689 0.01569 -0.0754 0.9284 1.0000
1.500 0.3218 0.02734 0.01606 -0.0767 0.9223 1.0000
1.750 0.3553 0.02785 0.01651 -0.0784 0.9169 1.0000
2.000 0.3831 0.02828 0.01692 -0.0791 0.9096 1.0000
2.250 0.4169 0.02877 0.01741 -0.0809 0.9037 1.0000
2.500 0.4449 0.02920 0.01789 -0.0815 0.8956 1.0000
2.750 0.4754 0.02964 0.01838 -0.0826 0.8879 1.0000
3.000 0.5088 0.03006 0.01888 -0.0841 0.8803 1.0000
3.250 0.5361 0.03047 0.01937 -0.0845 0.8707 1.0000
3.500 0.5685 0.03083 0.01986 -0.0856 0.8618 1.0000
3.750 0.6041 0.03111 0.02040 -0.0872 0.8528 1.0000
4.000 0.6331 0.03138 0.02084 -0.0875 0.8410 1.0000
4.250 0.6640 0.03154 0.02120 -0.0881 0.8286 1.0000
4.500 0.6972 0.03153 0.02152 -0.0887 0.8151 1.0000
4.750 0.7339 0.03121 0.02149 -0.0894 0.8001 1.0000
5.000 0.7638 0.03078 0.02135 -0.0888 0.7799 1.0000
5.250 0.8020 0.02962 0.02054 -0.0885 0.7565 1.0000
5.500 0.8280 0.02866 0.01989 -0.0862 0.7260 1.0000
5.750 0.8526 0.02765 0.01931 -0.0836 0.6898 1.0000
6.000 0.8743 0.02689 0.01884 -0.0807 0.6387 1.0000
6.250 0.9340 0.02461 0.01598 -0.0802 0.4540 1.0000
6.500 0.9396 0.02644 0.01679 -0.0762 0.3094 1.0000
6.750 0.9428 0.02856 0.01826 -0.0730 0.2217 1.0000
7.000 0.9515 0.03058 0.01986 -0.0707 0.1668 1.0000
7.250 0.9657 0.03247 0.02157 -0.0689 0.1323 1.0000
7.500 0.9834 0.03428 0.02331 -0.0677 0.1058 1.0000
7.750 1.0068 0.03624 0.02523 -0.0671 0.0864 1.0000
8.000 1.0398 0.03830 0.02753 -0.0674 0.0684 1.0000
8.250 1.0797 0.04117 0.03080 -0.0688 0.0549 1.0000
8.500 1.1108 0.04435 0.03424 -0.0692 0.0454 1.0000
8.750 1.1294 0.04700 0.03717 -0.0682 0.0385 1.0000
9.000 1.1527 0.05166 0.04229 -0.0675 0.0355 1.0000
9.250 1.1617 0.05567 0.04698 -0.0649 0.0328 1.0000
9.500 1.1637 0.05884 0.05057 -0.0621 0.0299 1.0000
9.750 1.1623 0.06137 0.05331 -0.0593 0.0276 1.0000
10.000 1.1576 0.06464 0.05675 -0.0566 0.0262 1.0000
10.250 1.1480 0.06879 0.06112 -0.0536 0.0258 1.0000
10.500 1.1349 0.07262 0.06532 -0.0506 0.0256 1.0000
10.750 1.1195 0.07668 0.06968 -0.0483 0.0256 1.0000
11.000 1.1024 0.08102 0.07430 -0.0467 0.0256 1.0000
11.250 1.0843 0.08571 0.07923 -0.0460 0.0256 1.0000
11.500 1.0660 0.09079 0.08451 -0.0463 0.0257 1.0000
11.750 1.0478 0.09631 0.09021 -0.0476 0.0258 1.0000
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Polar data table (+)
Polar graphs
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