MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 50,000 Max Cl/Cd: 33.08 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh64-il-50000-n5.txt Download as CSV file: xf-mh64-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 64 8.59%
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5552 0.09414 0.08770 0.0012 1.0000 0.0339
-8.500 -0.5564 0.08911 0.08274 -0.0020 1.0000 0.0331
-8.250 -0.5594 0.08360 0.07732 -0.0061 1.0000 0.0324
-8.000 -0.5645 0.07732 0.07111 -0.0117 1.0000 0.0314
-7.750 -0.5708 0.07004 0.06378 -0.0179 1.0000 0.0304
-7.500 -0.5769 0.06325 0.05683 -0.0228 1.0000 0.0293
-7.250 -0.5738 0.05821 0.05137 -0.0252 1.0000 0.0288
-6.750 -0.5553 0.04954 0.04190 -0.0273 1.0000 0.0284
-6.250 -0.5265 0.04141 0.03295 -0.0277 1.0000 0.0287
-6.000 -0.5087 0.03773 0.02887 -0.0276 1.0000 0.0293
-5.750 -0.4885 0.03467 0.02546 -0.0272 1.0000 0.0302
-5.500 -0.4669 0.03230 0.02280 -0.0268 1.0000 0.0328
-5.250 -0.4437 0.03019 0.02032 -0.0261 1.0000 0.0371
-5.000 -0.4197 0.02801 0.01777 -0.0252 1.0000 0.0409
-4.750 -0.3975 0.02601 0.01570 -0.0242 1.0000 0.0451
-4.500 -0.3749 0.02441 0.01391 -0.0231 1.0000 0.0545
-4.250 -0.3536 0.02275 0.01226 -0.0221 1.0000 0.0710
-4.000 -0.3319 0.02096 0.01064 -0.0214 1.0000 0.1167
-3.750 -0.3129 0.01924 0.00968 -0.0207 1.0000 0.2416
-3.500 -0.2968 0.01843 0.00932 -0.0190 1.0000 0.3531
-3.250 -0.2809 0.01786 0.00899 -0.0170 1.0000 0.4349
-3.000 -0.2646 0.01737 0.00864 -0.0149 1.0000 0.5040
-2.750 -0.2482 0.01691 0.00834 -0.0126 1.0000 0.5713
-2.500 -0.2321 0.01649 0.00810 -0.0101 1.0000 0.6446
-2.250 -0.2142 0.01612 0.00793 -0.0076 1.0000 0.7330
-2.000 -0.1686 0.01583 0.00767 -0.0098 0.9984 0.8702
-1.750 -0.0905 0.01573 0.00715 -0.0196 0.9958 1.0000
-1.500 -0.0469 0.01585 0.00689 -0.0237 0.9805 1.0000
-1.250 -0.0021 0.01598 0.00667 -0.0278 0.9666 1.0000
-1.000 0.0419 0.01611 0.00655 -0.0315 0.9528 1.0000
-0.750 0.0830 0.01625 0.00648 -0.0345 0.9381 1.0000
-0.500 0.1212 0.01640 0.00644 -0.0367 0.9227 1.0000
-0.250 0.1563 0.01656 0.00646 -0.0383 0.9067 1.0000
0.000 0.1884 0.01674 0.00652 -0.0390 0.8905 1.0000
0.250 0.2180 0.01692 0.00660 -0.0392 0.8743 1.0000
0.500 0.2435 0.01712 0.00673 -0.0386 0.8567 1.0000
0.750 0.2683 0.01733 0.00686 -0.0377 0.8394 1.0000
1.000 0.2926 0.01751 0.00699 -0.0366 0.8225 1.0000
1.250 0.3165 0.01769 0.00711 -0.0354 0.8060 1.0000
1.500 0.3392 0.01789 0.00731 -0.0341 0.7876 1.0000
1.750 0.3622 0.01806 0.00746 -0.0327 0.7697 1.0000
2.000 0.3854 0.01821 0.00759 -0.0312 0.7523 1.0000
2.250 0.4084 0.01838 0.00777 -0.0299 0.7329 1.0000
2.500 0.4315 0.01853 0.00792 -0.0285 0.7137 1.0000
2.750 0.4548 0.01867 0.00813 -0.0270 0.6939 1.0000
3.000 0.4781 0.01882 0.00832 -0.0257 0.6729 1.0000
3.250 0.5016 0.01897 0.00850 -0.0243 0.6510 1.0000
3.500 0.5251 0.01909 0.00864 -0.0228 0.6291 1.0000
3.750 0.5486 0.01927 0.00887 -0.0216 0.6043 1.0000
4.000 0.5724 0.01946 0.00916 -0.0203 0.5788 1.0000
4.250 0.5962 0.01968 0.00941 -0.0190 0.5521 1.0000
4.500 0.6199 0.01994 0.00969 -0.0178 0.5243 1.0000
4.750 0.6435 0.02025 0.01002 -0.0166 0.4954 1.0000
5.000 0.6669 0.02063 0.01039 -0.0154 0.4659 1.0000
5.250 0.6901 0.02110 0.01096 -0.0144 0.4348 1.0000
5.500 0.7130 0.02164 0.01153 -0.0134 0.4034 1.0000
5.750 0.7356 0.02224 0.01214 -0.0124 0.3723 1.0000
6.000 0.7578 0.02293 0.01284 -0.0115 0.3414 1.0000
6.250 0.7795 0.02371 0.01367 -0.0106 0.3096 1.0000
6.500 0.8007 0.02456 0.01456 -0.0098 0.2788 1.0000
6.750 0.8213 0.02552 0.01552 -0.0089 0.2494 1.0000
7.000 0.8411 0.02657 0.01670 -0.0080 0.2207 1.0000
7.250 0.8601 0.02774 0.01791 -0.0071 0.1921 1.0000
7.500 0.8782 0.02905 0.01924 -0.0062 0.1653 1.0000
7.750 0.8950 0.03053 0.02074 -0.0053 0.1405 1.0000
8.000 0.9105 0.03213 0.02241 -0.0044 0.1159 1.0000
8.250 0.9258 0.03408 0.02443 -0.0033 0.0975 1.0000
8.500 0.9388 0.03599 0.02644 -0.0023 0.0797 1.0000
8.750 0.9528 0.03835 0.02895 -0.0010 0.0684 1.0000
9.000 0.9646 0.04073 0.03147 0.0001 0.0589 1.0000
9.250 0.9729 0.04294 0.03368 0.0011 0.0510 1.0000
9.500 0.9848 0.04626 0.03748 0.0024 0.0464 1.0000
9.750 0.9921 0.04945 0.04098 0.0035 0.0428 1.0000
10.000 0.9961 0.05226 0.04380 0.0044 0.0395 1.0000
10.250 0.9901 0.05591 0.04787 0.0054 0.0373 1.0000
10.500 0.9801 0.05968 0.05198 0.0059 0.0359 1.0000
10.750 0.9682 0.06396 0.05654 0.0054 0.0352 1.0000
11.000 0.9532 0.06893 0.06176 0.0036 0.0348 1.0000
11.250 0.9366 0.07470 0.06772 0.0007 0.0351 1.0000
11.500 0.9180 0.08144 0.07464 -0.0034 0.0356 1.0000
11.750 0.8994 0.08904 0.08236 -0.0083 0.0365 1.0000
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Polar data table (+)
Polar graphs
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