MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 50,000 Max Cl/Cd: 12.29 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh80-il-50000.txt Download as CSV file: xf-mh80-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 80 12.72%
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4461 0.11242 0.10695 0.0228 1.0000 0.2423
-8.500 -0.4215 0.10714 0.10171 0.0236 1.0000 0.2506
-8.250 -0.4485 0.10631 0.10108 0.0197 1.0000 0.2605
-8.000 -0.4223 0.10147 0.09626 0.0211 1.0000 0.2755
-7.750 -0.4034 0.09712 0.09199 0.0215 1.0000 0.2885
-7.500 -0.3953 0.09361 0.08858 0.0211 1.0000 0.3026
-7.250 -0.3903 0.09032 0.08542 0.0203 1.0000 0.3171
-7.000 -0.3830 0.08697 0.08219 0.0199 1.0000 0.3340
-6.000 -0.4428 0.05854 0.05331 -0.0185 1.0000 0.1426
-5.750 -0.4599 0.05771 0.05261 -0.0149 1.0000 0.1407
-5.500 -0.4324 0.05114 0.04547 -0.0208 0.9809 0.1234
-5.250 -0.3844 0.04421 0.03744 -0.0280 0.9592 0.1119
-5.000 -0.3348 0.03948 0.03213 -0.0330 0.9359 0.1090
-4.750 -0.2888 0.03599 0.02797 -0.0361 0.9128 0.1098
-4.500 -0.2566 0.03381 0.02516 -0.0362 0.8873 0.1146
-4.250 -0.2263 0.03200 0.02326 -0.0356 0.8645 0.1220
-4.000 -0.2012 0.03062 0.02159 -0.0341 0.8411 0.1320
-3.750 -0.1760 0.02934 0.02026 -0.0323 0.8201 0.1502
-3.500 -0.1507 0.02806 0.01905 -0.0304 0.8009 0.1833
-3.250 -0.1264 0.02619 0.01768 -0.0284 0.7832 0.2748
-3.000 -0.1189 0.02366 0.01690 -0.0237 0.7676 0.5020
-2.750 0.0852 0.02400 0.01719 -0.0389 0.7321 1.0000
-2.500 0.0995 0.02397 0.01683 -0.0381 0.7156 1.0000
-2.250 0.1167 0.02408 0.01664 -0.0374 0.6995 1.0000
-2.000 0.1349 0.02430 0.01658 -0.0366 0.6839 1.0000
-1.750 0.1546 0.02460 0.01662 -0.0360 0.6690 1.0000
-1.500 0.1746 0.02499 0.01677 -0.0353 0.6551 1.0000
-1.250 0.1940 0.02539 0.01693 -0.0343 0.6425 1.0000
-1.000 0.2128 0.02576 0.01704 -0.0328 0.6309 1.0000
-0.750 0.2350 0.02641 0.01755 -0.0328 0.6176 1.0000
-0.500 0.2559 0.02706 0.01803 -0.0322 0.6062 1.0000
-0.250 0.2751 0.02750 0.01824 -0.0305 0.5966 1.0000
0.000 0.2974 0.02845 0.01911 -0.0309 0.5845 1.0000
0.250 0.3172 0.02910 0.01959 -0.0297 0.5758 1.0000
0.500 0.3382 0.03007 0.02047 -0.0296 0.5652 1.0000
0.750 0.3583 0.03109 0.02140 -0.0292 0.5561 1.0000
1.000 0.3780 0.03200 0.02220 -0.0284 0.5474 1.0000
1.250 0.3971 0.03337 0.02352 -0.0284 0.5390 1.0000
1.500 0.4158 0.03447 0.02455 -0.0278 0.5308 1.0000
1.750 0.4333 0.03586 0.02588 -0.0273 0.5233 1.0000
2.000 0.4488 0.03769 0.02771 -0.0276 0.5153 1.0000
2.250 0.4693 0.03820 0.02806 -0.0254 0.5102 1.0000
2.500 0.4745 0.04175 0.03174 -0.0276 0.5019 1.0000
2.750 0.4907 0.04302 0.03293 -0.0265 0.4958 1.0000
3.000 0.5011 0.04525 0.03514 -0.0262 0.4906 1.0000
3.250 0.4918 0.04969 0.03964 -0.0279 0.4866 1.0000
3.500 0.4874 0.05308 0.04302 -0.0283 0.4831 1.0000
3.750 0.4930 0.05555 0.04544 -0.0279 0.4797 1.0000
4.000 0.5150 0.05687 0.04668 -0.0265 0.4754 1.0000
4.250 0.5100 0.06070 0.05051 -0.0273 0.4762 1.0000
5.000 0.3491 0.07786 0.06770 -0.0345 0.6186 1.0000
5.250 0.3694 0.08077 0.07057 -0.0349 0.6107 1.0000
5.500 0.3849 0.08276 0.07251 -0.0346 0.5975 1.0000
5.750 0.3856 0.08420 0.07390 -0.0334 0.5854 1.0000
6.000 0.4247 0.08865 0.07833 -0.0351 0.5783 1.0000
6.250 0.4119 0.08881 0.07844 -0.0331 0.5659 1.0000
6.500 0.4300 0.09192 0.08153 -0.0334 0.5591 1.0000
6.750 0.4415 0.09380 0.08339 -0.0330 0.5466 1.0000
7.000 0.4424 0.09557 0.08514 -0.0323 0.5364 1.0000
7.250 0.4703 0.09908 0.08864 -0.0330 0.5282 1.0000
7.500 0.4633 0.10033 0.08987 -0.0322 0.5191 1.0000
7.750 0.4910 0.10397 0.09351 -0.0329 0.5112 1.0000
8.000 0.4841 0.10519 0.09471 -0.0321 0.5011 1.0000
8.250 0.5168 0.10946 0.09902 -0.0330 0.4936 1.0000
8.500 0.5044 0.11017 0.09969 -0.0322 0.4836 1.0000
8.750 0.5321 0.11419 0.10376 -0.0329 0.4772 1.0000
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Polar data table (+)
Polar graphs
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