MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MILEY M06-13-128 (miley-il) Reynolds number: 500,000 Max Cl/Cd: 121.43 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-miley-il-500000-n5.txt Download as CSV file: xf-miley-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MILEY M06-13-128
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2112 0.08670 0.08297 -0.0110 0.5309 0.0075
-8.000 -0.2082 0.08293 0.07920 -0.0124 0.5306 0.0075
-7.750 -0.2053 0.07925 0.07554 -0.0139 0.5304 0.0075
-7.500 -0.2038 0.07533 0.07164 -0.0154 0.5303 0.0075
-7.250 -0.2025 0.07160 0.06793 -0.0170 0.5301 0.0075
-7.000 -0.2022 0.06786 0.06423 -0.0186 0.5299 0.0075
-6.750 -0.2043 0.06412 0.06052 -0.0204 0.5296 0.0075
-6.500 -0.2099 0.06053 0.05696 -0.0224 0.5293 0.0075
-6.250 -0.2077 0.05619 0.05261 -0.0257 0.5289 0.0075
-6.000 -0.2024 0.05168 0.04807 -0.0287 0.5286 0.0075
-5.750 -0.1945 0.04699 0.04333 -0.0314 0.5282 0.0075
-5.250 -0.1716 0.03776 0.03393 -0.0354 0.5275 0.0075
-4.750 -0.1526 0.04190 0.03739 -0.0413 0.5272 0.0045
-4.500 -0.1326 0.03832 0.03361 -0.0415 0.5268 0.0044
-4.250 -0.1115 0.03468 0.02973 -0.0413 0.5264 0.0043
-4.000 -0.0896 0.03105 0.02582 -0.0407 0.5260 0.0042
-3.750 -0.0670 0.02736 0.02177 -0.0396 0.5256 0.0042
-3.500 -0.0437 0.02355 0.01751 -0.0381 0.5252 0.0043
-3.250 -0.0194 0.01979 0.01319 -0.0363 0.5248 0.0047
-3.000 0.0060 0.01807 0.01116 -0.0356 0.5244 0.0051
-2.750 0.0329 0.01743 0.01038 -0.0354 0.5238 0.0054
-2.500 0.0602 0.01700 0.00985 -0.0352 0.5232 0.0060
-2.250 0.0876 0.01632 0.00900 -0.0349 0.5226 0.0069
-2.000 0.1146 0.01543 0.00795 -0.0344 0.5221 0.0071
-1.750 0.1413 0.01469 0.00710 -0.0339 0.5216 0.0072
-1.500 0.1679 0.01413 0.00645 -0.0335 0.5211 0.0074
-1.250 0.1942 0.01359 0.00585 -0.0331 0.5207 0.0078
-1.000 0.2212 0.01330 0.00554 -0.0329 0.5202 0.0087
-0.750 0.2486 0.01306 0.00526 -0.0327 0.5197 0.0108
-0.500 0.2760 0.01284 0.00499 -0.0325 0.5192 0.0139
-0.250 0.3036 0.01272 0.00485 -0.0325 0.5186 0.0195
0.000 0.3314 0.01264 0.00473 -0.0324 0.5182 0.0228
0.250 0.3591 0.01259 0.00464 -0.0324 0.5176 0.0286
0.500 0.3855 0.01231 0.00462 -0.0322 0.5171 0.1237
0.750 0.4075 0.01147 0.00465 -0.0316 0.5164 0.4248
1.250 0.5303 0.01007 0.00478 -0.0462 0.5144 1.0000
1.500 0.5567 0.01016 0.00484 -0.0460 0.5132 1.0000
1.750 0.5832 0.01023 0.00488 -0.0457 0.5120 1.0000
2.000 0.6097 0.01030 0.00492 -0.0456 0.5108 1.0000
2.250 0.6364 0.01035 0.00494 -0.0454 0.5096 1.0000
2.500 0.6632 0.01037 0.00493 -0.0452 0.5084 1.0000
2.750 0.6902 0.01035 0.00487 -0.0450 0.5071 1.0000
3.000 0.7173 0.01028 0.00475 -0.0449 0.5057 1.0000
3.250 0.7447 0.01017 0.00456 -0.0447 0.5041 1.0000
3.500 0.7715 0.01016 0.00461 -0.0446 0.5012 1.0000
3.750 0.7985 0.01016 0.00464 -0.0445 0.4986 1.0000
4.000 0.8255 0.01019 0.00468 -0.0445 0.4969 1.0000
4.250 0.8526 0.01020 0.00470 -0.0444 0.4954 1.0000
4.500 0.8799 0.01019 0.00470 -0.0444 0.4939 1.0000
4.750 0.9072 0.01015 0.00466 -0.0444 0.4925 1.0000
5.000 0.9345 0.01014 0.00465 -0.0443 0.4913 1.0000
5.250 0.9613 0.01025 0.00484 -0.0444 0.4890 1.0000
5.500 0.9882 0.01035 0.00503 -0.0444 0.4861 1.0000
5.750 1.0154 0.01036 0.00509 -0.0444 0.4832 1.0000
6.000 1.0429 0.01031 0.00508 -0.0445 0.4806 1.0000
6.250 1.0704 0.01025 0.00506 -0.0445 0.4784 1.0000
6.500 1.0970 0.01043 0.00535 -0.0446 0.4737 1.0000
6.750 1.1243 0.01043 0.00541 -0.0447 0.4694 1.0000
7.000 1.1517 0.01038 0.00540 -0.0447 0.4648 1.0000
7.250 1.1789 0.01039 0.00550 -0.0448 0.4573 1.0000
7.500 1.2062 0.01034 0.00548 -0.0449 0.4492 1.0000
7.750 1.2332 0.01030 0.00544 -0.0449 0.4381 1.0000
8.000 1.2592 0.01037 0.00548 -0.0449 0.4216 1.0000
8.250 1.2833 0.01068 0.00571 -0.0447 0.4014 1.0000
8.500 1.3063 0.01117 0.00616 -0.0444 0.3816 1.0000
8.750 1.3275 0.01185 0.00678 -0.0441 0.3599 1.0000
9.000 1.3476 0.01265 0.00753 -0.0437 0.3368 1.0000
9.250 1.3669 0.01349 0.00835 -0.0434 0.3182 1.0000
9.500 1.3843 0.01451 0.00933 -0.0429 0.2968 1.0000
9.750 1.3896 0.01669 0.01132 -0.0422 0.2566 1.0000
10.000 1.3867 0.02053 0.01504 -0.0435 0.2219 1.0000
10.250 1.3721 0.02474 0.01922 -0.0439 0.2067 1.0000
10.500 1.3576 0.02803 0.02245 -0.0426 0.1917 1.0000
10.750 1.3426 0.03139 0.02569 -0.0415 0.1692 1.0000
11.000 1.3304 0.03452 0.02869 -0.0404 0.1464 1.0000
11.250 1.3176 0.03769 0.03169 -0.0393 0.1204 1.0000
11.500 1.3042 0.04095 0.03479 -0.0382 0.0942 1.0000
11.750 1.2914 0.04434 0.03799 -0.0373 0.0678 1.0000
12.000 1.2830 0.04755 0.04105 -0.0367 0.0441 1.0000
12.250 1.2767 0.05064 0.04403 -0.0361 0.0252 1.0000
12.500 1.2765 0.05326 0.04663 -0.0358 0.0165 1.0000
12.750 1.2741 0.05615 0.04948 -0.0355 0.0080 1.0000
13.000 1.2722 0.05908 0.05242 -0.0353 0.0037 1.0000
13.250 1.2742 0.06164 0.05503 -0.0352 0.0025 1.0000
13.500 1.2781 0.06401 0.05747 -0.0351 0.0018 1.0000
13.750 1.2820 0.06643 0.05996 -0.0351 0.0017 1.0000
14.000 1.2848 0.06902 0.06265 -0.0351 0.0016 1.0000
14.250 1.2845 0.07204 0.06576 -0.0351 0.0012 1.0000
14.500 1.2860 0.07484 0.06865 -0.0353 0.0009 1.0000
14.750 1.2869 0.07780 0.07171 -0.0354 0.0010 1.0000
15.000 1.2875 0.08083 0.07482 -0.0357 0.0009 1.0000
15.250 1.2852 0.08428 0.07837 -0.0361 0.0007 1.0000
15.500 1.2850 0.08747 0.08165 -0.0364 0.0007 1.0000
15.750 1.2843 0.09081 0.08509 -0.0369 0.0008 1.0000
16.000 1.2763 0.09525 0.08964 -0.0376 0.0005 1.0000
16.250 1.2743 0.09885 0.09333 -0.0383 0.0006 1.0000
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Polar data table (+)
Polar graphs
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