MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MILEY M06-13-128 (miley-il) Reynolds number: 1,000,000 Max Cl/Cd: 157.64 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-miley-il-1000000-n5.txt Download as CSV file: xf-miley-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2546 0.08641 0.08307 -0.0170 0.5166 0.0046
-7.500 -0.2528 0.08303 0.07972 -0.0186 0.5165 0.0047
-7.250 -0.2517 0.07989 0.07661 -0.0200 0.5164 0.0047
-7.000 -0.2549 0.07685 0.07361 -0.0213 0.5162 0.0047
-6.750 -0.2538 0.07339 0.07017 -0.0239 0.5161 0.0047
-6.500 -0.2478 0.06945 0.06623 -0.0273 0.5159 0.0047
-6.250 -0.2391 0.06549 0.06225 -0.0304 0.5157 0.0047
-6.000 -0.2281 0.06140 0.05813 -0.0333 0.5155 0.0047
-5.000 -0.1736 0.04194 0.03820 -0.0408 0.5147 0.0026
-4.750 -0.1550 0.03753 0.03360 -0.0412 0.5143 0.0025
-4.500 -0.1351 0.03326 0.02910 -0.0409 0.5140 0.0024
-4.250 -0.1148 0.02871 0.02424 -0.0400 0.5136 0.0024
-4.000 -0.0953 0.02304 0.01808 -0.0380 0.5133 0.0024
-3.750 -0.0795 0.01476 0.00875 -0.0341 0.5131 0.0030
-3.500 -0.0529 0.01394 0.00778 -0.0337 0.5127 0.0032
-3.250 -0.0257 0.01346 0.00720 -0.0335 0.5124 0.0033
-3.000 0.0013 0.01288 0.00652 -0.0332 0.5120 0.0036
-2.750 0.0281 0.01225 0.00577 -0.0329 0.5116 0.0037
-2.500 0.0550 0.01172 0.00514 -0.0325 0.5113 0.0039
-2.250 0.0822 0.01134 0.00470 -0.0323 0.5109 0.0041
-2.000 0.1094 0.01101 0.00430 -0.0320 0.5105 0.0044
-1.750 0.1373 0.01083 0.00409 -0.0320 0.5101 0.0047
-1.500 0.1642 0.01043 0.00362 -0.0316 0.5096 0.0050
-1.250 0.1917 0.01016 0.00330 -0.0314 0.5091 0.0053
-1.000 0.2195 0.00998 0.00310 -0.0313 0.5087 0.0059
-0.750 0.2475 0.00984 0.00294 -0.0313 0.5083 0.0072
-0.500 0.2756 0.00974 0.00285 -0.0313 0.5079 0.0102
-0.250 0.3038 0.00967 0.00276 -0.0313 0.5075 0.0126
0.000 0.3320 0.00959 0.00269 -0.0313 0.5070 0.0155
0.250 0.3603 0.00953 0.00261 -0.0314 0.5065 0.0181
0.500 0.3885 0.00946 0.00253 -0.0314 0.5060 0.0210
0.750 0.4163 0.00934 0.00249 -0.0314 0.5055 0.0530
1.000 0.4421 0.00892 0.00247 -0.0312 0.5048 0.2133
1.250 0.4646 0.00824 0.00250 -0.0305 0.5039 0.4822
1.500 0.4883 0.00692 0.00255 -0.0297 0.5032 0.9302
2.000 0.6190 0.00688 0.00249 -0.0462 0.5007 1.0000
2.250 0.6460 0.00683 0.00243 -0.0460 0.4986 1.0000
2.500 0.6733 0.00675 0.00231 -0.0459 0.4961 1.0000
2.750 0.7006 0.00668 0.00222 -0.0458 0.4939 1.0000
3.000 0.7278 0.00667 0.00218 -0.0457 0.4926 1.0000
3.250 0.7549 0.00669 0.00218 -0.0456 0.4915 1.0000
3.500 0.7821 0.00673 0.00223 -0.0455 0.4903 1.0000
3.750 0.8094 0.00676 0.00228 -0.0455 0.4887 1.0000
4.000 0.8366 0.00680 0.00233 -0.0455 0.4872 1.0000
4.250 0.8640 0.00683 0.00238 -0.0454 0.4855 1.0000
4.500 0.8914 0.00685 0.00243 -0.0455 0.4835 1.0000
4.750 0.9188 0.00685 0.00244 -0.0455 0.4813 1.0000
5.000 0.9463 0.00684 0.00243 -0.0455 0.4790 1.0000
5.250 0.9736 0.00689 0.00251 -0.0455 0.4764 1.0000
5.500 1.0010 0.00693 0.00260 -0.0456 0.4730 1.0000
5.750 1.0285 0.00695 0.00263 -0.0456 0.4691 1.0000
6.000 1.0559 0.00696 0.00266 -0.0457 0.4643 1.0000
6.250 1.0833 0.00699 0.00271 -0.0458 0.4563 1.0000
6.500 1.1103 0.00706 0.00275 -0.0458 0.4450 1.0000
6.750 1.1366 0.00721 0.00286 -0.0458 0.4302 1.0000
7.000 1.1620 0.00750 0.00309 -0.0457 0.4107 1.0000
7.250 1.1864 0.00794 0.00345 -0.0456 0.3881 1.0000
7.500 1.2108 0.00837 0.00383 -0.0455 0.3687 1.0000
7.750 1.2352 0.00881 0.00423 -0.0454 0.3513 1.0000
8.000 1.2585 0.00937 0.00472 -0.0452 0.3312 1.0000
8.250 1.2818 0.00992 0.00522 -0.0450 0.3109 1.0000
8.500 1.3048 0.01048 0.00575 -0.0449 0.2935 1.0000
8.750 1.3266 0.01117 0.00637 -0.0447 0.2737 1.0000
9.000 1.3427 0.01246 0.00745 -0.0442 0.2338 1.0000
9.250 1.3539 0.01421 0.00891 -0.0435 0.1856 1.0000
9.500 1.3554 0.01694 0.01133 -0.0430 0.1302 1.0000
9.750 1.3418 0.02297 0.01720 -0.0466 0.0875 1.0000
10.000 1.3336 0.02570 0.01994 -0.0454 0.0807 1.0000
10.250 1.3158 0.02931 0.02344 -0.0441 0.0590 1.0000
10.500 1.3021 0.03259 0.02660 -0.0430 0.0378 1.0000
10.750 1.2956 0.03530 0.02926 -0.0421 0.0231 1.0000
11.000 1.2965 0.03739 0.03133 -0.0414 0.0159 1.0000
11.250 1.2931 0.03989 0.03379 -0.0406 0.0075 1.0000
11.500 1.2974 0.04179 0.03571 -0.0401 0.0046 1.0000
11.750 1.3018 0.04377 0.03770 -0.0396 0.0025 1.0000
12.000 1.3070 0.04575 0.03972 -0.0393 0.0015 1.0000
12.250 1.3136 0.04763 0.04164 -0.0390 0.0010 1.0000
12.500 1.3216 0.04936 0.04342 -0.0388 0.0009 1.0000
12.750 1.3272 0.05138 0.04549 -0.0385 0.0007 1.0000
13.000 1.3322 0.05352 0.04769 -0.0383 0.0005 1.0000
13.250 1.3386 0.05551 0.04974 -0.0382 0.0005 1.0000
13.500 1.3433 0.05770 0.05199 -0.0380 0.0003 1.0000
13.750 1.3470 0.06007 0.05441 -0.0379 0.0003 1.0000
14.000 1.3539 0.06209 0.05650 -0.0379 0.0004 1.0000
14.250 1.3516 0.06518 0.05967 -0.0378 0.0002 1.0000
14.500 1.3531 0.06790 0.06246 -0.0378 0.0002 1.0000
14.750 1.3547 0.07066 0.06530 -0.0378 0.0002 1.0000
15.000 1.3568 0.07338 0.06809 -0.0380 0.0002 1.0000
15.250 1.3573 0.07631 0.07109 -0.0381 0.0002 1.0000
15.500 1.3572 0.07940 0.07426 -0.0384 0.0002 1.0000
15.750 1.3584 0.08234 0.07727 -0.0387 0.0002 1.0000
16.000 1.3536 0.08616 0.08119 -0.0391 0.0001 1.0000
16.250 1.3542 0.08923 0.08433 -0.0396 0.0001 1.0000
16.500 1.3492 0.09316 0.08838 -0.0401 0.0001 1.0000
16.750 1.3434 0.09730 0.09261 -0.0408 0.0001 1.0000
17.000 1.3407 0.10100 0.09640 -0.0416 0.0001 1.0000
17.250 1.3382 0.10469 0.10016 -0.0423 0.0001 1.0000
17.500 1.3284 0.10955 0.10514 -0.0434 0.0001 1.0000
17.750 1.3245 0.11361 0.10928 -0.0445 0.0001 1.0000
18.000 1.3223 0.11740 0.11315 -0.0455 0.0001 1.0000
18.250 1.3150 0.12203 0.11788 -0.0468 0.0001 1.0000
18.500 1.3062 0.12698 0.12293 -0.0483 0.0001 1.0000
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Polar data table (+)
Polar graphs
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