MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 50,000 Max Cl/Cd: 31.95 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh121-il-50000.txt Download as CSV file: xf-mh121-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 121 8.76%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4349 0.09939 0.09324 -0.0211 1.0000 0.2746
-7.250 -0.4426 0.09756 0.09136 -0.0186 1.0000 0.2886
-7.000 -0.4513 0.09584 0.08975 -0.0157 1.0000 0.3024
-6.750 -0.4607 0.09419 0.08821 -0.0125 1.0000 0.3161
-6.500 -0.4683 0.09222 0.08635 -0.0092 1.0000 0.3308
-6.250 -0.4699 0.09028 0.08449 -0.0052 1.0000 0.3561
-6.000 -0.4609 0.08732 0.08156 -0.0019 1.0000 0.3816
-5.750 -0.4528 0.08430 0.07858 0.0012 1.0000 0.4058
-4.750 -0.4384 0.04952 0.04243 -0.0539 1.0000 0.1145
-4.500 -0.4082 0.04430 0.03656 -0.0567 1.0000 0.0989
-4.250 -0.3730 0.04038 0.03129 -0.0592 1.0000 0.0907
-4.000 -0.3435 0.03721 0.02755 -0.0602 1.0000 0.0913
-3.750 -0.3155 0.03401 0.02410 -0.0607 1.0000 0.0933
-3.500 -0.2855 0.03159 0.02113 -0.0605 1.0000 0.0927
-3.250 -0.2582 0.02937 0.01872 -0.0597 1.0000 0.0959
-3.000 -0.2317 0.02765 0.01673 -0.0583 1.0000 0.1034
-2.750 -0.2073 0.02595 0.01509 -0.0572 1.0000 0.1303
-2.500 -0.1753 0.02161 0.01373 -0.0567 1.0000 0.5878
-2.250 -0.1861 0.02198 0.01445 -0.0448 1.0000 0.7379
-2.000 -0.1935 0.02184 0.01437 -0.0350 1.0000 0.8119
-1.750 -0.2025 0.02130 0.01391 -0.0253 1.0000 0.8852
-1.500 -0.1652 0.02051 0.01279 -0.0266 1.0000 1.0000
-1.250 -0.1321 0.02034 0.01211 -0.0307 1.0000 1.0000
-1.000 -0.0954 0.02040 0.01155 -0.0350 1.0000 1.0000
-0.750 -0.0604 0.02059 0.01130 -0.0384 1.0000 1.0000
-0.500 -0.0281 0.02085 0.01117 -0.0410 1.0000 1.0000
-0.250 0.0015 0.02116 0.01115 -0.0428 1.0000 1.0000
0.000 0.0292 0.02150 0.01122 -0.0440 1.0000 1.0000
0.250 0.0555 0.02188 0.01135 -0.0449 1.0000 1.0000
0.500 0.0807 0.02228 0.01145 -0.0455 1.0000 1.0000
0.750 0.1051 0.02271 0.01171 -0.0459 1.0000 1.0000
1.000 0.1289 0.02317 0.01204 -0.0463 1.0000 1.0000
1.250 0.1521 0.02366 0.01242 -0.0465 1.0000 1.0000
1.500 0.1749 0.02418 0.01286 -0.0467 1.0000 1.0000
1.750 0.1972 0.02472 0.01336 -0.0468 1.0000 1.0000
2.000 0.2191 0.02531 0.01392 -0.0468 1.0000 1.0000
2.250 0.2406 0.02593 0.01452 -0.0469 1.0000 1.0000
2.500 0.2616 0.02659 0.01519 -0.0469 1.0000 1.0000
2.750 0.2822 0.02729 0.01591 -0.0469 1.0000 1.0000
3.000 0.3024 0.02804 0.01671 -0.0469 1.0000 1.0000
3.250 0.3221 0.02884 0.01758 -0.0469 1.0000 1.0000
3.500 0.3413 0.02970 0.01860 -0.0469 1.0000 1.0000
3.750 0.3600 0.03063 0.01963 -0.0469 1.0000 1.0000
4.000 0.3781 0.03162 0.02074 -0.0470 1.0000 1.0000
4.250 0.3956 0.03270 0.02195 -0.0471 1.0000 1.0000
4.500 0.4124 0.03386 0.02326 -0.0472 1.0000 1.0000
4.750 0.4374 0.03541 0.02502 -0.0492 0.9951 1.0000
5.000 0.5067 0.03783 0.02805 -0.0589 0.9606 1.0000
5.250 0.5705 0.03932 0.03007 -0.0664 0.9242 1.0000
5.500 0.6536 0.03955 0.03106 -0.0745 0.8753 1.0000
5.750 0.8380 0.02623 0.01650 -0.0682 0.2382 1.0000
6.250 0.9420 0.03630 0.02528 -0.0726 0.0895 1.0000
6.500 0.9746 0.04059 0.02961 -0.0729 0.0738 1.0000
6.750 0.9974 0.04353 0.03331 -0.0708 0.0689 1.0000
7.000 1.0200 0.04771 0.03806 -0.0690 0.0689 1.0000
7.250 1.0371 0.05207 0.04295 -0.0667 0.0704 1.0000
7.500 1.0516 0.05685 0.04810 -0.0647 0.0726 1.0000
7.750 1.0572 0.06078 0.05284 -0.0609 0.0781 1.0000
8.000 1.0602 0.06586 0.05840 -0.0582 0.0838 1.0000
8.250 1.0572 0.07067 0.06380 -0.0550 0.0926 1.0000
8.500 1.0530 0.07605 0.06960 -0.0526 0.1039 1.0000
8.750 1.0518 0.08315 0.07707 -0.0515 0.1272 1.0000
9.000 1.0181 0.08684 0.08106 -0.0491 0.1305 1.0000
9.250 0.9924 0.09214 0.08652 -0.0485 0.1430 1.0000
9.500 0.9638 0.09830 0.09278 -0.0504 0.1556 1.0000
9.750 0.8821 0.09734 0.09209 -0.0400 0.1250 1.0000
10.000 0.8501 0.10344 0.09824 -0.0426 0.1247 1.0000
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Polar data table (+)
Polar graphs
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