MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MILEY M06-13-128 (miley-il) Reynolds number: 1,000,000 Max Cl/Cd: 167.96 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-miley-il-1000000.txt Download as CSV file: xf-miley-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2645 0.08615 0.08301 -0.0167 0.5359 0.0069
-7.500 -0.2626 0.08291 0.07980 -0.0182 0.5356 0.0069
-7.250 -0.2624 0.07975 0.07666 -0.0196 0.5352 0.0072
-7.000 -0.2666 0.07681 0.07375 -0.0208 0.5349 0.0071
-6.750 -0.2659 0.07344 0.07040 -0.0236 0.5345 0.0075
-6.500 -0.2603 0.06964 0.06659 -0.0269 0.5343 0.0076
-6.250 -0.2520 0.06558 0.06250 -0.0303 0.5340 0.0078
-6.000 -0.2407 0.06123 0.05810 -0.0335 0.5336 0.0080
-5.750 -0.2249 0.05667 0.05345 -0.0366 0.5333 0.0083
-5.500 -0.2073 0.05242 0.04909 -0.0385 0.5329 0.0084
-5.250 -0.1896 0.04867 0.04523 -0.0396 0.5325 0.0085
-5.000 -0.1709 0.04503 0.04146 -0.0403 0.5319 0.0085
-4.750 -0.1514 0.04133 0.03759 -0.0405 0.5315 0.0086
-4.500 -0.1312 0.03784 0.03392 -0.0404 0.5314 0.0086
-4.250 -0.1105 0.03454 0.03040 -0.0400 0.5312 0.0086
-4.000 -0.0969 0.02951 0.02510 -0.0395 0.5309 0.0091
-3.750 -0.0744 0.02769 0.02314 -0.0392 0.5305 0.0093
-3.500 -0.0509 0.02591 0.02120 -0.0387 0.5301 0.0097
-3.250 -0.0266 0.02406 0.01916 -0.0381 0.5297 0.0101
-3.000 -0.0014 0.02226 0.01714 -0.0373 0.5293 0.0108
-2.750 0.0277 0.02179 0.01645 -0.0365 0.5289 0.0123
-2.500 0.0492 0.01630 0.01034 -0.0340 0.5285 0.0079
-2.250 0.0755 0.01454 0.00832 -0.0330 0.5281 0.0077
-2.000 0.1031 0.01393 0.00758 -0.0326 0.5275 0.0084
-1.750 0.1288 0.01296 0.00653 -0.0320 0.5269 0.0093
-1.500 0.1559 0.01260 0.00616 -0.0318 0.5263 0.0098
-1.250 0.1833 0.01236 0.00590 -0.0316 0.5257 0.0107
-1.000 0.2109 0.01218 0.00570 -0.0315 0.5251 0.0117
-0.750 0.2385 0.01197 0.00545 -0.0313 0.5245 0.0124
-0.500 0.2644 0.01143 0.00485 -0.0308 0.5239 0.0150
-0.250 0.2924 0.01131 0.00472 -0.0307 0.5232 0.0177
0.000 0.3198 0.01109 0.00446 -0.0305 0.5226 0.0236
0.250 0.3477 0.01099 0.00434 -0.0304 0.5219 0.0315
0.500 0.3712 0.01024 0.00427 -0.0299 0.5212 0.2731
0.750 0.3878 0.00910 0.00427 -0.0280 0.5206 0.6678
1.000 0.4779 0.00839 0.00433 -0.0414 0.5197 0.9928
1.250 0.5291 0.00857 0.00443 -0.0466 0.5185 1.0000
1.500 0.5551 0.00871 0.00455 -0.0463 0.5174 1.0000
1.750 0.5817 0.00867 0.00449 -0.0460 0.5166 1.0000
2.000 0.6084 0.00861 0.00442 -0.0458 0.5154 1.0000
2.250 0.6353 0.00852 0.00431 -0.0455 0.5136 1.0000
2.500 0.6623 0.00838 0.00413 -0.0453 0.5115 1.0000
2.750 0.6894 0.00825 0.00398 -0.0451 0.5097 1.0000
3.000 0.7165 0.00820 0.00390 -0.0450 0.5085 1.0000
3.250 0.7436 0.00820 0.00387 -0.0448 0.5075 1.0000
3.500 0.7707 0.00819 0.00383 -0.0447 0.5065 1.0000
3.750 0.7978 0.00823 0.00384 -0.0446 0.5054 1.0000
4.000 0.8246 0.00838 0.00399 -0.0445 0.5040 1.0000
4.250 0.8517 0.00836 0.00399 -0.0445 0.5032 1.0000
4.500 0.8789 0.00835 0.00402 -0.0444 0.5020 1.0000
4.750 0.9061 0.00834 0.00404 -0.0444 0.5005 1.0000
5.000 0.9335 0.00830 0.00404 -0.0444 0.4988 1.0000
5.250 0.9609 0.00824 0.00400 -0.0444 0.4970 1.0000
5.500 0.9885 0.00818 0.00395 -0.0444 0.4955 1.0000
5.750 1.0161 0.00812 0.00390 -0.0444 0.4940 1.0000
6.000 1.0438 0.00804 0.00383 -0.0445 0.4924 1.0000
6.250 1.0712 0.00802 0.00382 -0.0445 0.4904 1.0000
6.500 1.0986 0.00799 0.00387 -0.0446 0.4879 1.0000
6.750 1.1262 0.00794 0.00389 -0.0447 0.4851 1.0000
7.000 1.1539 0.00787 0.00386 -0.0448 0.4822 1.0000
7.250 1.1817 0.00777 0.00379 -0.0449 0.4792 1.0000
7.500 1.2093 0.00776 0.00386 -0.0450 0.4747 1.0000
7.750 1.2370 0.00772 0.00387 -0.0452 0.4685 1.0000
8.000 1.2646 0.00769 0.00389 -0.0453 0.4609 1.0000
8.250 1.2916 0.00769 0.00387 -0.0454 0.4433 1.0000
8.500 1.3148 0.00816 0.00416 -0.0451 0.4031 1.0000
8.750 1.3341 0.00918 0.00495 -0.0446 0.3563 1.0000
9.000 1.3519 0.01039 0.00594 -0.0441 0.3080 1.0000
9.250 1.3678 0.01176 0.00706 -0.0435 0.2627 1.0000
9.500 1.3842 0.01300 0.00812 -0.0431 0.2283 1.0000
9.750 1.3985 0.01437 0.00934 -0.0426 0.1961 1.0000
10.000 1.4076 0.01628 0.01107 -0.0422 0.1599 1.0000
10.250 1.4061 0.02086 0.01551 -0.0452 0.1212 1.0000
10.500 1.3864 0.02522 0.01983 -0.0449 0.1040 1.0000
10.750 1.3667 0.02901 0.02352 -0.0436 0.0843 1.0000
11.250 1.3409 0.03545 0.02976 -0.0415 0.0466 1.0000
11.500 1.3224 0.03916 0.03331 -0.0402 0.0221 1.0000
11.750 1.3132 0.04221 0.03628 -0.0393 0.0087 1.0000
12.000 1.3086 0.04508 0.03915 -0.0387 0.0038 1.0000
12.250 1.3134 0.04714 0.04126 -0.0383 0.0033 1.0000
12.500 1.3203 0.04899 0.04317 -0.0380 0.0031 1.0000
12.750 1.3250 0.05112 0.04535 -0.0377 0.0027 1.0000
13.000 1.3276 0.05352 0.04781 -0.0375 0.0024 1.0000
13.250 1.3237 0.05663 0.05102 -0.0371 0.0019 1.0000
13.500 1.3254 0.05923 0.05370 -0.0370 0.0019 1.0000
13.750 1.3279 0.06178 0.05632 -0.0369 0.0018 1.0000
14.000 1.3288 0.06454 0.05918 -0.0369 0.0018 1.0000
14.250 1.3281 0.06755 0.06226 -0.0369 0.0017 1.0000
14.500 1.3266 0.07073 0.06553 -0.0370 0.0016 1.0000
14.750 1.3246 0.07402 0.06890 -0.0371 0.0016 1.0000
15.000 1.3235 0.07723 0.07220 -0.0373 0.0016 1.0000
15.250 1.3214 0.08063 0.07568 -0.0377 0.0016 1.0000
15.500 1.3170 0.08442 0.07956 -0.0381 0.0016 1.0000
15.750 1.3099 0.08861 0.08384 -0.0386 0.0015 1.0000
16.000 1.3059 0.09242 0.08774 -0.0391 0.0015 1.0000
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Polar data table (+)
Polar graphs
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