MH 94 16.03% (mh94-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 94 16.03% (mh94-il) Reynolds number: 50,000 Max Cl/Cd: 27.28 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh94-il-50000-n5.txt Download as CSV file: xf-mh94-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 94 16.03%
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5738 0.10143 0.09308 -0.0563 1.0000 0.0469
-13.250 -0.6045 0.09265 0.08417 -0.0607 1.0000 0.0463
-13.000 -0.6346 0.08510 0.07646 -0.0642 1.0000 0.0458
-12.750 -0.6607 0.07896 0.07014 -0.0665 1.0000 0.0455
-12.500 -0.6825 0.07396 0.06495 -0.0676 1.0000 0.0455
-12.250 -0.7006 0.06977 0.06058 -0.0678 1.0000 0.0457
-12.000 -0.7158 0.06613 0.05674 -0.0674 1.0000 0.0460
-11.750 -0.7295 0.06290 0.05331 -0.0663 1.0000 0.0466
-11.500 -0.7388 0.06007 0.05028 -0.0648 1.0000 0.0470
-11.250 -0.7502 0.05737 0.04729 -0.0628 1.0000 0.0478
-11.000 -0.7498 0.05530 0.04514 -0.0609 1.0000 0.0488
-10.750 -0.7457 0.05355 0.04336 -0.0589 1.0000 0.0500
-10.500 -0.7415 0.05174 0.04144 -0.0569 1.0000 0.0514
-10.250 -0.7337 0.04995 0.03947 -0.0548 1.0000 0.0529
-10.000 -0.7218 0.04827 0.03758 -0.0528 1.0000 0.0547
-9.750 -0.7120 0.04697 0.03634 -0.0508 1.0000 0.0569
-9.500 -0.7027 0.04566 0.03494 -0.0485 1.0000 0.0598
-9.250 -0.6931 0.04440 0.03364 -0.0462 1.0000 0.0629
-9.000 -0.6871 0.04321 0.03245 -0.0436 1.0000 0.0660
-8.750 -0.6818 0.04203 0.03118 -0.0407 1.0000 0.0700
-8.500 -0.6838 0.04085 0.03007 -0.0372 1.0000 0.0733
-8.250 -0.6848 0.03976 0.02888 -0.0335 1.0000 0.0779
-8.000 -0.6891 0.03856 0.02778 -0.0296 1.0000 0.0820
-7.750 -0.6900 0.03738 0.02658 -0.0260 1.0000 0.0885
-7.500 -0.6928 0.03608 0.02536 -0.0223 1.0000 0.0957
-7.250 -0.6948 0.03475 0.02412 -0.0187 1.0000 0.1052
-7.000 -0.6962 0.03335 0.02284 -0.0152 1.0000 0.1193
-6.750 -0.6977 0.03183 0.02155 -0.0117 1.0000 0.1410
-6.500 -0.6988 0.03020 0.02029 -0.0085 1.0000 0.1787
-6.250 -0.6985 0.02867 0.01922 -0.0053 1.0000 0.2369
-6.000 -0.6941 0.02757 0.01856 -0.0024 1.0000 0.3049
-5.750 -0.6855 0.02695 0.01824 0.0004 1.0000 0.3656
-5.500 -0.6742 0.02668 0.01816 0.0031 1.0000 0.4160
-5.250 -0.6616 0.02661 0.01815 0.0057 1.0000 0.4594
-5.000 -0.6482 0.02672 0.01830 0.0084 1.0000 0.4973
-4.750 -0.6336 0.02706 0.01869 0.0113 1.0000 0.5278
-4.500 -0.6120 0.02738 0.01895 0.0126 0.9974 0.5557
-4.250 -0.5789 0.02796 0.01944 0.0120 0.9905 0.5778
-4.000 -0.5450 0.02836 0.01969 0.0110 0.9835 0.5965
-3.750 -0.5134 0.02859 0.01977 0.0103 0.9758 0.6135
-3.500 -0.4801 0.02881 0.01984 0.0091 0.9685 0.6301
-3.250 -0.4487 0.02909 0.02002 0.0087 0.9604 0.6441
-3.000 -0.4172 0.02933 0.02016 0.0082 0.9524 0.6573
-2.750 -0.3843 0.02946 0.02017 0.0071 0.9444 0.6715
-2.500 -0.3562 0.02946 0.02005 0.0068 0.9351 0.6855
-2.250 -0.3194 0.02974 0.02026 0.0055 0.9277 0.6964
-2.000 -0.2939 0.02965 0.02007 0.0057 0.9172 0.7091
-1.750 -0.2607 0.02974 0.02010 0.0048 0.9087 0.7206
-1.500 -0.2306 0.02974 0.02003 0.0044 0.8987 0.7316
-1.250 -0.2029 0.02964 0.01984 0.0041 0.8883 0.7442
-1.000 -0.1660 0.02971 0.01989 0.0029 0.8799 0.7537
-0.750 -0.1417 0.02956 0.01967 0.0032 0.8678 0.7661
-0.500 -0.1048 0.02957 0.01965 0.0020 0.8593 0.7755
-0.250 -0.0787 0.02942 0.01947 0.0022 0.8471 0.7871
0.000 -0.0505 0.02936 0.01939 0.0024 0.8354 0.7975
0.250 -0.0121 0.02914 0.01915 0.0009 0.8265 0.8080
0.500 0.0119 0.02902 0.01901 0.0017 0.8127 0.8192
0.750 0.0436 0.02884 0.01884 0.0014 0.8009 0.8292
1.000 0.0808 0.02845 0.01844 0.0003 0.7908 0.8405
1.250 0.1101 0.02829 0.01830 0.0005 0.7766 0.8500
1.500 0.1412 0.02796 0.01798 0.0004 0.7638 0.8614
1.750 0.1892 0.02749 0.01752 -0.0022 0.7534 0.8696
2.250 0.2557 0.02691 0.01700 -0.0031 0.7218 0.8904
2.500 0.2955 0.02656 0.01667 -0.0046 0.7056 0.8997
2.750 0.3368 0.02621 0.01633 -0.0064 0.6881 0.9093
3.000 0.3808 0.02588 0.01600 -0.0087 0.6684 0.9175
3.250 0.4206 0.02557 0.01568 -0.0103 0.6469 0.9271
3.500 0.4703 0.02526 0.01533 -0.0135 0.6228 0.9339
3.750 0.5054 0.02518 0.01523 -0.0147 0.5950 0.9440
4.000 0.5514 0.02508 0.01500 -0.0176 0.5645 0.9511
4.250 0.5890 0.02514 0.01496 -0.0194 0.5312 0.9602
4.750 0.6602 0.02556 0.01512 -0.0229 0.4618 0.9799
5.000 0.6937 0.02591 0.01531 -0.0245 0.4276 0.9909
5.250 0.7174 0.02630 0.01553 -0.0245 0.3989 1.0000
5.500 0.7162 0.02653 0.01566 -0.0200 0.3804 1.0000
5.750 0.7144 0.02678 0.01582 -0.0154 0.3628 1.0000
6.000 0.7140 0.02707 0.01601 -0.0110 0.3457 1.0000
6.250 0.7173 0.02746 0.01628 -0.0073 0.3284 1.0000
6.500 0.7249 0.02796 0.01667 -0.0044 0.3109 1.0000
6.750 0.7359 0.02855 0.01716 -0.0021 0.2938 1.0000
7.000 0.7485 0.02922 0.01773 -0.0002 0.2773 1.0000
7.250 0.7632 0.02997 0.01838 0.0014 0.2621 1.0000
7.500 0.7791 0.03076 0.01910 0.0028 0.2484 1.0000
7.750 0.7961 0.03159 0.01979 0.0039 0.2363 1.0000
8.000 0.8134 0.03248 0.02069 0.0050 0.2242 1.0000
8.250 0.8325 0.03342 0.02163 0.0058 0.2141 1.0000
8.500 0.8514 0.03435 0.02248 0.0066 0.2052 1.0000
8.750 0.8699 0.03540 0.02359 0.0074 0.1966 1.0000
9.000 0.8897 0.03640 0.02454 0.0081 0.1896 1.0000
9.250 0.9096 0.03756 0.02576 0.0086 0.1833 1.0000
9.500 0.9272 0.03872 0.02701 0.0094 0.1772 1.0000
9.750 0.9499 0.03978 0.02797 0.0096 0.1723 1.0000
10.000 0.9634 0.04123 0.02963 0.0108 0.1673 1.0000
10.250 0.9786 0.04265 0.03118 0.0118 0.1630 1.0000
10.500 0.9970 0.04394 0.03249 0.0123 0.1593 1.0000
10.750 1.0168 0.04533 0.03388 0.0127 0.1560 1.0000
11.000 1.0202 0.04730 0.03614 0.0146 0.1527 1.0000
11.250 1.0255 0.04923 0.03827 0.0161 0.1497 1.0000
11.500 1.0334 0.05104 0.04020 0.0173 0.1469 1.0000
11.750 1.0458 0.05276 0.04200 0.0180 0.1446 1.0000
12.000 1.0647 0.05436 0.04356 0.0183 0.1424 1.0000
12.250 1.0489 0.05756 0.04711 0.0205 0.1408 1.0000
12.500 1.0295 0.06129 0.05115 0.0221 0.1394 1.0000
12.750 1.0041 0.06585 0.05601 0.0229 0.1382 1.0000
13.000 0.9654 0.07221 0.06266 0.0224 0.1371 1.0000
13.250 0.8028 0.09895 0.08989 0.0090 0.1372 1.0000
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Polar data table (+)
Polar graphs
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