MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MILEY M06-13-128 (miley-il) Reynolds number: 500,000 Max Cl/Cd: 122.83 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-miley-il-500000.txt Download as CSV file: xf-miley-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2645 0.08928 0.08572 -0.0189 0.5614 0.0123
-7.500 -0.2619 0.08606 0.08252 -0.0208 0.5611 0.0123
-7.250 -0.2625 0.08278 0.07929 -0.0229 0.5609 0.0123
-7.000 -0.2625 0.07965 0.07618 -0.0254 0.5606 0.0123
-6.750 -0.2565 0.07585 0.07236 -0.0287 0.5602 0.0124
-6.500 -0.2480 0.07201 0.06850 -0.0319 0.5599 0.0124
-6.250 -0.2377 0.06811 0.06455 -0.0346 0.5595 0.0124
-6.000 -0.2255 0.06409 0.06047 -0.0370 0.5592 0.0124
-5.750 -0.2185 0.05853 0.05484 -0.0391 0.5589 0.0126
-5.500 -0.2091 0.05472 0.05098 -0.0401 0.5584 0.0129
-5.250 -0.1939 0.05165 0.04785 -0.0410 0.5578 0.0131
-5.000 -0.1769 0.04879 0.04491 -0.0417 0.5574 0.0134
-4.750 -0.1584 0.04595 0.04196 -0.0423 0.5569 0.0139
-4.500 -0.1382 0.04305 0.03891 -0.0428 0.5563 0.0144
-4.250 -0.1169 0.04016 0.03586 -0.0429 0.5558 0.0150
-4.000 -0.0941 0.03733 0.03283 -0.0427 0.5552 0.0159
-3.750 -0.0659 0.03547 0.03068 -0.0418 0.5546 0.0175
-3.500 -0.0409 0.03392 0.02881 -0.0410 0.5537 0.0178
-3.250 -0.0239 0.02891 0.02341 -0.0402 0.5529 0.0188
-3.000 -0.0005 0.02728 0.02171 -0.0400 0.5521 0.0196
-2.750 0.0243 0.02595 0.02023 -0.0396 0.5515 0.0209
-2.500 0.0504 0.02474 0.01879 -0.0390 0.5508 0.0230
-2.250 0.0803 0.02565 0.01945 -0.0383 0.5501 0.0256
-2.000 0.1050 0.02062 0.01395 -0.0365 0.5495 0.0168
-1.750 0.1320 0.01915 0.01226 -0.0358 0.5488 0.0164
-1.500 0.1595 0.01859 0.01154 -0.0354 0.5480 0.0184
-1.250 0.1860 0.01772 0.01058 -0.0349 0.5474 0.0185
-1.000 0.2121 0.01713 0.00993 -0.0343 0.5467 0.0185
-0.750 0.2369 0.01659 0.00935 -0.0336 0.5460 0.0200
-0.500 0.2629 0.01644 0.00920 -0.0333 0.5449 0.0229
-0.250 0.2894 0.01620 0.00897 -0.0331 0.5435 0.0285
0.000 0.3164 0.01614 0.00893 -0.0330 0.5419 0.0354
0.250 0.3383 0.01530 0.00890 -0.0323 0.5403 0.2945
0.500 0.4415 0.01345 0.00898 -0.0486 0.5389 1.0000
0.750 0.4669 0.01358 0.00902 -0.0482 0.5376 1.0000
1.000 0.4925 0.01367 0.00903 -0.0478 0.5364 1.0000
1.250 0.5183 0.01374 0.00903 -0.0474 0.5355 1.0000
1.500 0.5443 0.01379 0.00899 -0.0470 0.5345 1.0000
1.750 0.5703 0.01388 0.00900 -0.0466 0.5336 1.0000
2.000 0.5962 0.01401 0.00907 -0.0462 0.5327 1.0000
2.250 0.6216 0.01434 0.00935 -0.0459 0.5313 1.0000
2.500 0.6472 0.01453 0.00963 -0.0460 0.5279 1.0000
2.750 0.6734 0.01456 0.00965 -0.0457 0.5254 1.0000
3.000 0.7001 0.01446 0.00951 -0.0454 0.5235 1.0000
3.250 0.7274 0.01423 0.00921 -0.0451 0.5220 1.0000
3.500 0.7549 0.01398 0.00889 -0.0448 0.5205 1.0000
3.750 0.7822 0.01384 0.00868 -0.0445 0.5192 1.0000
4.000 0.8090 0.01392 0.00872 -0.0443 0.5182 1.0000
4.250 0.8345 0.01414 0.00904 -0.0443 0.5153 1.0000
4.500 0.8607 0.01423 0.00918 -0.0442 0.5126 1.0000
4.750 0.8877 0.01418 0.00914 -0.0441 0.5107 1.0000
5.000 0.9149 0.01412 0.00909 -0.0440 0.5091 1.0000
5.250 0.9423 0.01402 0.00899 -0.0439 0.5078 1.0000
5.500 0.9699 0.01389 0.00886 -0.0438 0.5066 1.0000
5.750 0.9978 0.01373 0.00867 -0.0437 0.5054 1.0000
6.000 1.0257 0.01361 0.00854 -0.0437 0.5042 1.0000
6.250 1.0509 0.01376 0.00885 -0.0437 0.5001 1.0000
6.500 1.0779 0.01368 0.00883 -0.0436 0.4973 1.0000
6.750 1.1058 0.01346 0.00865 -0.0436 0.4952 1.0000
7.000 1.1342 0.01315 0.00836 -0.0436 0.4934 1.0000
7.250 1.1629 0.01281 0.00802 -0.0437 0.4917 1.0000
7.500 1.1892 0.01280 0.00814 -0.0437 0.4879 1.0000
7.750 1.2164 0.01268 0.00813 -0.0437 0.4838 1.0000
8.000 1.2447 0.01235 0.00786 -0.0438 0.4806 1.0000
8.250 1.2732 0.01201 0.00756 -0.0438 0.4774 1.0000
8.500 1.2998 0.01199 0.00771 -0.0439 0.4698 1.0000
8.750 1.3280 0.01172 0.00753 -0.0440 0.4632 1.0000
9.000 1.3559 0.01146 0.00734 -0.0441 0.4504 1.0000
9.250 1.3818 0.01125 0.00698 -0.0439 0.4170 1.0000
9.500 1.3953 0.01251 0.00783 -0.0429 0.3567 1.0000
9.750 1.4052 0.01430 0.00936 -0.0419 0.3072 1.0000
10.000 1.4134 0.01618 0.01110 -0.0412 0.2727 1.0000
10.250 1.4210 0.01813 0.01299 -0.0409 0.2487 1.0000
10.500 1.4211 0.02199 0.01687 -0.0432 0.2288 1.0000
10.750 1.4053 0.02565 0.02051 -0.0423 0.2179 1.0000
11.000 1.3916 0.02895 0.02375 -0.0413 0.2023 1.0000
11.250 1.3843 0.03171 0.02647 -0.0404 0.1888 1.0000
11.500 1.3669 0.03531 0.02991 -0.0392 0.1621 1.0000
11.750 1.3489 0.03895 0.03335 -0.0381 0.1316 1.0000
12.000 1.3217 0.04349 0.03755 -0.0368 0.0890 1.0000
12.250 1.3080 0.04713 0.04101 -0.0360 0.0610 1.0000
12.500 1.2953 0.05083 0.04451 -0.0354 0.0345 1.0000
12.750 1.2762 0.05542 0.04892 -0.0348 0.0114 1.0000
13.000 1.2725 0.05855 0.05208 -0.0344 0.0076 1.0000
13.250 1.2720 0.06142 0.05502 -0.0343 0.0062 1.0000
13.500 1.2663 0.06495 0.05866 -0.0341 0.0054 1.0000
13.750 1.2682 0.06766 0.06145 -0.0341 0.0052 1.0000
14.000 1.2681 0.07066 0.06456 -0.0342 0.0050 1.0000
14.250 1.2663 0.07394 0.06793 -0.0343 0.0045 1.0000
14.500 1.2632 0.07743 0.07151 -0.0345 0.0042 1.0000
14.750 1.2604 0.08094 0.07511 -0.0348 0.0039 1.0000
15.000 1.2571 0.08460 0.07887 -0.0352 0.0039 1.0000
15.250 1.2538 0.08826 0.08263 -0.0357 0.0039 1.0000
15.500 1.2498 0.09210 0.08656 -0.0362 0.0039 1.0000
15.750 1.2313 0.09797 0.09253 -0.0370 0.0035 1.0000
16.000 1.2277 0.10181 0.09644 -0.0376 0.0035 1.0000
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Polar data table (+)
Polar graphs
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