MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 45 9.85% (mh45-il) Reynolds number: 50,000 Max Cl/Cd: 27.9 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh45-il-50000.txt Download as CSV file: xf-mh45-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 45 9.85%
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5105 0.10241 0.09640 0.0181 1.0000 0.2679
-8.000 -0.5021 0.09800 0.09205 0.0174 1.0000 0.2732
-7.750 -0.5180 0.09625 0.09045 0.0148 1.0000 0.2843
-7.500 -0.4970 0.09067 0.08487 0.0150 1.0000 0.2874
-7.250 -0.4904 0.08678 0.08104 0.0140 1.0000 0.2922
-7.000 -0.5531 0.06644 0.06050 -0.0199 1.0000 0.1287
-6.750 -0.5493 0.05876 0.05244 -0.0241 1.0000 0.1115
-6.500 -0.5378 0.05345 0.04695 -0.0254 1.0000 0.1063
-6.250 -0.5301 0.04710 0.03976 -0.0272 1.0000 0.0983
-6.000 -0.5132 0.04278 0.03509 -0.0272 1.0000 0.0961
-5.750 -0.4952 0.03879 0.03062 -0.0269 1.0000 0.0945
-5.500 -0.4755 0.03530 0.02662 -0.0262 1.0000 0.0948
-5.250 -0.4554 0.03253 0.02324 -0.0251 1.0000 0.0987
-5.000 -0.4361 0.03020 0.02087 -0.0239 1.0000 0.1057
-4.750 -0.4168 0.02809 0.01831 -0.0220 1.0000 0.1130
-4.500 -0.4001 0.02631 0.01656 -0.0201 1.0000 0.1282
-4.250 -0.3835 0.02466 0.01505 -0.0181 1.0000 0.1515
-4.000 -0.3680 0.02292 0.01364 -0.0158 1.0000 0.2028
-3.750 -0.3587 0.02102 0.01258 -0.0124 1.0000 0.3431
-3.500 -0.3520 0.02044 0.01245 -0.0085 1.0000 0.4441
-3.250 -0.3428 0.02003 0.01239 -0.0047 1.0000 0.5226
-3.000 -0.3304 0.01949 0.01210 -0.0012 1.0000 0.5958
-2.750 -0.3168 0.01888 0.01174 0.0023 1.0000 0.6724
-2.500 -0.3026 0.01828 0.01149 0.0065 1.0000 0.7684
-2.250 -0.1053 0.01807 0.01053 -0.0212 1.0000 1.0000
-2.000 -0.1320 0.01778 0.01006 -0.0160 1.0000 1.0000
-1.750 -0.1320 0.01785 0.00983 -0.0134 1.0000 1.0000
-1.500 -0.1247 0.01804 0.00971 -0.0116 1.0000 1.0000
-1.250 -0.1141 0.01830 0.00972 -0.0102 1.0000 1.0000
-1.000 -0.1017 0.01863 0.00981 -0.0091 1.0000 1.0000
-0.750 -0.0847 0.01904 0.01000 -0.0088 0.9987 1.0000
-0.500 -0.0251 0.01996 0.01063 -0.0164 0.9826 1.0000
-0.250 0.0290 0.02077 0.01123 -0.0227 0.9654 1.0000
0.000 0.0834 0.02156 0.01184 -0.0288 0.9479 1.0000
0.250 0.1411 0.02231 0.01248 -0.0352 0.9305 1.0000
0.500 0.1933 0.02297 0.01307 -0.0404 0.9125 1.0000
0.750 0.2407 0.02358 0.01363 -0.0445 0.8936 1.0000
1.000 0.2877 0.02414 0.01417 -0.0481 0.8752 1.0000
1.250 0.3294 0.02469 0.01471 -0.0504 0.8569 1.0000
1.500 0.3558 0.02534 0.01535 -0.0502 0.8367 1.0000
1.750 0.3879 0.02587 0.01588 -0.0504 0.8180 1.0000
2.000 0.4166 0.02639 0.01641 -0.0499 0.7997 1.0000
2.250 0.4367 0.02707 0.01712 -0.0484 0.7794 1.0000
2.500 0.4621 0.02753 0.01759 -0.0470 0.7608 1.0000
2.750 0.4879 0.02786 0.01794 -0.0454 0.7434 1.0000
3.000 0.5058 0.02857 0.01868 -0.0436 0.7224 1.0000
3.250 0.5289 0.02892 0.01910 -0.0417 0.7038 1.0000
3.500 0.5530 0.02908 0.01929 -0.0395 0.6863 1.0000
3.750 0.5729 0.02962 0.01989 -0.0376 0.6657 1.0000
4.000 0.5954 0.02982 0.02014 -0.0354 0.6465 1.0000
4.250 0.6199 0.02968 0.02007 -0.0328 0.6288 1.0000
4.500 0.6404 0.03011 0.02058 -0.0309 0.6071 1.0000
4.750 0.6644 0.02995 0.02046 -0.0283 0.5877 1.0000
5.000 0.6874 0.02993 0.02053 -0.0259 0.5670 1.0000
5.250 0.7108 0.02986 0.02051 -0.0234 0.5452 1.0000
5.500 0.7340 0.02986 0.02056 -0.0211 0.5228 1.0000
5.750 0.7587 0.02958 0.02027 -0.0185 0.5003 1.0000
6.000 0.7811 0.02987 0.02066 -0.0165 0.4748 1.0000
6.250 0.8043 0.03009 0.02088 -0.0145 0.4495 1.0000
6.500 0.8281 0.03028 0.02103 -0.0124 0.4239 1.0000
6.750 0.8522 0.03055 0.02120 -0.0104 0.3984 1.0000
7.000 0.8737 0.03136 0.02206 -0.0089 0.3713 1.0000
7.250 0.8946 0.03242 0.02323 -0.0076 0.3454 1.0000
7.500 0.9157 0.03352 0.02435 -0.0062 0.3211 1.0000
7.750 0.9390 0.03443 0.02515 -0.0048 0.2988 1.0000
8.000 0.9564 0.03621 0.02715 -0.0037 0.2770 1.0000
8.250 0.9776 0.03769 0.02866 -0.0026 0.2581 1.0000
8.500 0.9964 0.03939 0.03047 -0.0015 0.2397 1.0000
8.750 1.0122 0.04182 0.03313 -0.0005 0.2248 1.0000
9.000 1.0265 0.04421 0.03573 0.0006 0.2100 1.0000
9.250 1.0404 0.04669 0.03839 0.0016 0.1967 1.0000
9.500 1.0572 0.04925 0.04101 0.0026 0.1850 1.0000
9.750 1.0473 0.05399 0.04638 0.0034 0.1786 1.0000
10.000 1.0555 0.05694 0.04945 0.0044 0.1688 1.0000
10.250 1.0348 0.06263 0.05552 0.0045 0.1674 1.0000
10.500 1.0046 0.06891 0.06202 0.0038 0.1681 1.0000
10.750 0.9696 0.07561 0.06876 0.0021 0.1700 1.0000
11.000 0.9401 0.08356 0.07669 -0.0015 0.1716 1.0000
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Polar data table (+)
Polar graphs
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