MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: MILEY M06-13-128 (miley-il) Reynolds number: 200,000 Max Cl/Cd: 62.75 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-miley-il-200000-n5.txt Download as CSV file: xf-miley-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2597 0.09652 0.09171 -0.0155 0.5616 0.0160
-7.750 -0.2554 0.09336 0.08858 -0.0174 0.5612 0.0160
-7.500 -0.2530 0.09007 0.08532 -0.0200 0.5607 0.0162
-7.250 -0.2505 0.08683 0.08212 -0.0222 0.5603 0.0163
-7.000 -0.2511 0.08379 0.07910 -0.0245 0.5598 0.0163
-6.750 -0.2456 0.08013 0.07543 -0.0281 0.5594 0.0164
-6.500 -0.2374 0.07634 0.07161 -0.0314 0.5590 0.0164
-6.250 -0.2272 0.07258 0.06779 -0.0342 0.5587 0.0164
-6.000 -0.2153 0.06877 0.06393 -0.0367 0.5583 0.0165
-5.750 -0.2019 0.06496 0.06002 -0.0388 0.5578 0.0165
-5.500 -0.1872 0.06116 0.05613 -0.0406 0.5573 0.0165
-5.250 -0.1713 0.05756 0.05241 -0.0418 0.5567 0.0165
-5.000 -0.1543 0.05393 0.04862 -0.0428 0.5562 0.0165
-4.750 -0.1364 0.05051 0.04503 -0.0434 0.5555 0.0165
-4.500 -0.1254 0.04500 0.03945 -0.0438 0.5547 0.0108
-4.250 -0.1056 0.04181 0.03605 -0.0440 0.5538 0.0104
-4.000 -0.0841 0.03866 0.03262 -0.0439 0.5529 0.0102
-3.750 -0.0606 0.03546 0.02907 -0.0433 0.5522 0.0106
-3.500 -0.0374 0.03278 0.02602 -0.0427 0.5515 0.0120
-3.250 -0.0136 0.03183 0.02495 -0.0428 0.5508 0.0140
-3.000 0.0114 0.02948 0.02219 -0.0420 0.5501 0.0137
-2.750 0.0372 0.02735 0.01966 -0.0411 0.5494 0.0131
-2.500 0.0638 0.02557 0.01750 -0.0403 0.5486 0.0127
-2.250 0.0908 0.02417 0.01577 -0.0396 0.5478 0.0126
-2.000 0.1179 0.02308 0.01445 -0.0391 0.5470 0.0128
-1.750 0.1449 0.02217 0.01337 -0.0386 0.5463 0.0132
-1.500 0.1716 0.02143 0.01250 -0.0382 0.5457 0.0139
-1.250 0.1978 0.02083 0.01181 -0.0377 0.5452 0.0150
-1.000 0.2235 0.02030 0.01121 -0.0372 0.5446 0.0177
-0.750 0.2494 0.02013 0.01110 -0.0371 0.5428 0.0224
-0.500 0.2751 0.01995 0.01092 -0.0370 0.5411 0.0284
-0.250 0.3015 0.01995 0.01085 -0.0369 0.5397 0.0335
0.000 0.3276 0.01983 0.01079 -0.0367 0.5382 0.0538
0.250 0.3445 0.01850 0.01084 -0.0355 0.5368 0.4632
0.750 0.4672 0.01753 0.01093 -0.0491 0.5345 1.0000
1.000 0.4927 0.01770 0.01097 -0.0487 0.5335 1.0000
1.250 0.5182 0.01787 0.01103 -0.0483 0.5325 1.0000
1.500 0.5438 0.01803 0.01109 -0.0480 0.5317 1.0000
1.750 0.5695 0.01819 0.01114 -0.0476 0.5308 1.0000
2.000 0.5936 0.01890 0.01192 -0.0479 0.5273 1.0000
2.250 0.6183 0.01934 0.01237 -0.0478 0.5246 1.0000
2.500 0.6436 0.01961 0.01260 -0.0476 0.5227 1.0000
2.750 0.6692 0.01975 0.01270 -0.0473 0.5211 1.0000
3.000 0.6951 0.01983 0.01272 -0.0470 0.5198 1.0000
3.250 0.7213 0.01985 0.01269 -0.0466 0.5186 1.0000
3.500 0.7477 0.01981 0.01259 -0.0462 0.5176 1.0000
4.000 0.7954 0.02076 0.01368 -0.0463 0.5093 1.0000
4.250 0.8219 0.02065 0.01354 -0.0459 0.5072 1.0000
4.500 0.8491 0.02038 0.01324 -0.0455 0.5057 1.0000
4.750 0.8768 0.02007 0.01290 -0.0451 0.5044 1.0000
5.250 0.9234 0.02103 0.01407 -0.0452 0.4951 1.0000
5.500 0.9501 0.02090 0.01396 -0.0449 0.4933 1.0000
5.750 0.9773 0.02069 0.01378 -0.0447 0.4920 1.0000
6.250 1.0226 0.02172 0.01506 -0.0447 0.4819 1.0000
6.500 1.0498 0.02147 0.01488 -0.0445 0.4801 1.0000
6.750 1.0769 0.02124 0.01470 -0.0443 0.4783 1.0000
7.250 1.1220 0.02208 0.01580 -0.0443 0.4669 1.0000
7.750 1.1576 0.02430 0.01836 -0.0449 0.4493 1.0000
8.000 1.1804 0.02462 0.01879 -0.0449 0.4430 1.0000
8.500 1.2279 0.02489 0.01925 -0.0448 0.4292 1.0000
8.750 1.2494 0.02529 0.01976 -0.0449 0.4199 1.0000
9.000 1.2824 0.02389 0.01842 -0.0440 0.4154 1.0000
9.250 1.3095 0.02332 0.01790 -0.0434 0.4063 1.0000
9.500 1.3408 0.02219 0.01678 -0.0425 0.3968 1.0000
9.750 1.3661 0.02177 0.01636 -0.0417 0.3852 1.0000
10.000 1.3836 0.02215 0.01672 -0.0408 0.3692 1.0000
10.250 1.3914 0.02351 0.01805 -0.0401 0.3517 1.0000
10.500 1.3850 0.02605 0.02054 -0.0391 0.3368 1.0000
10.750 1.3817 0.02825 0.02270 -0.0380 0.3232 1.0000
11.000 1.3767 0.03061 0.02497 -0.0368 0.3074 1.0000
11.250 1.3680 0.03327 0.02750 -0.0356 0.2890 1.0000
11.500 1.3576 0.03621 0.03034 -0.0346 0.2688 1.0000
11.750 1.3456 0.03926 0.03323 -0.0336 0.2483 1.0000
12.000 1.3355 0.04228 0.03614 -0.0328 0.2270 1.0000
12.250 1.3236 0.04548 0.03920 -0.0320 0.2049 1.0000
12.500 1.3197 0.04820 0.04186 -0.0316 0.1859 1.0000
12.750 1.3080 0.05185 0.04532 -0.0312 0.1555 1.0000
13.000 1.2922 0.05604 0.04924 -0.0310 0.1191 1.0000
13.250 1.2766 0.06035 0.05329 -0.0308 0.0876 1.0000
13.500 1.2625 0.06465 0.05740 -0.0307 0.0601 1.0000
13.750 1.2568 0.06814 0.06083 -0.0307 0.0445 1.0000
14.000 1.2424 0.07280 0.06533 -0.0310 0.0247 1.0000
14.250 1.2306 0.07735 0.06982 -0.0314 0.0142 1.0000
14.500 1.2250 0.08124 0.07379 -0.0318 0.0102 1.0000
14.750 1.2198 0.08518 0.07783 -0.0322 0.0078 1.0000
15.000 1.2145 0.08922 0.08196 -0.0328 0.0067 1.0000
15.250 1.2087 0.09345 0.08632 -0.0336 0.0059 1.0000
15.500 1.2055 0.09734 0.09035 -0.0344 0.0055 1.0000
15.750 1.2018 0.10139 0.09454 -0.0352 0.0052 1.0000
16.000 1.1963 0.10577 0.09903 -0.0363 0.0045 1.0000
16.250 1.1925 0.10998 0.10338 -0.0374 0.0046 1.0000
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Polar data table (+)
Polar graphs
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