GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 585 AIRFOIL (goe585-il) Reynolds number: 50,000 Max Cl/Cd: 37.42 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe585-il-50000-n5.txt Download as CSV file: xf-goe585-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 585 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3906 0.10266 0.09557 -0.0250 1.0000 0.1216
-8.250 -0.4043 0.10111 0.09418 -0.0267 1.0000 0.1231
-8.000 -0.4147 0.09896 0.09216 -0.0282 1.0000 0.1236
-7.750 -0.3947 0.09397 0.08715 -0.0249 1.0000 0.1273
-7.500 -0.4147 0.08665 0.07987 -0.0351 1.0000 0.0797
-7.250 -0.4057 0.08337 0.07663 -0.0321 1.0000 0.0780
-7.000 -0.4027 0.07993 0.07323 -0.0319 1.0000 0.0758
-6.750 -0.4016 0.07623 0.06957 -0.0328 1.0000 0.0738
-6.500 -0.4003 0.07220 0.06555 -0.0344 1.0000 0.0720
-6.250 -0.3970 0.06836 0.06169 -0.0357 1.0000 0.0718
-6.000 -0.3916 0.06466 0.05793 -0.0368 1.0000 0.0726
-5.750 -0.3844 0.06083 0.05400 -0.0379 1.0000 0.0733
-5.500 -0.3753 0.05676 0.04978 -0.0390 1.0000 0.0731
-5.250 -0.3641 0.05252 0.04530 -0.0401 1.0000 0.0722
-5.000 -0.3506 0.04845 0.04093 -0.0409 1.0000 0.0718
-4.750 -0.3353 0.04485 0.03700 -0.0414 1.0000 0.0721
-4.500 -0.3185 0.04191 0.03371 -0.0414 1.0000 0.0746
-4.250 -0.2998 0.03888 0.03021 -0.0415 1.0000 0.0766
-4.000 -0.2800 0.03613 0.02699 -0.0413 1.0000 0.0772
-3.750 -0.2590 0.03371 0.02410 -0.0409 1.0000 0.0779
-3.500 -0.2372 0.03164 0.02152 -0.0403 1.0000 0.0789
-3.250 -0.2151 0.02991 0.01937 -0.0397 1.0000 0.0802
-3.000 -0.1950 0.02891 0.01833 -0.0389 1.0000 0.0836
-2.750 -0.1736 0.02801 0.01725 -0.0382 1.0000 0.0881
-2.500 -0.1509 0.02698 0.01590 -0.0374 1.0000 0.0914
-2.250 -0.1167 0.02591 0.01446 -0.0387 0.9954 0.0948
-2.000 -0.0813 0.02512 0.01362 -0.0405 0.9888 0.0997
-1.750 -0.0440 0.02446 0.01269 -0.0422 0.9823 0.1080
-1.500 -0.0057 0.02397 0.01210 -0.0444 0.9757 0.1237
-1.250 0.0301 0.02341 0.01162 -0.0463 0.9676 0.1516
-1.000 0.0676 0.02278 0.01126 -0.0485 0.9590 0.2035
-0.750 0.1081 0.02200 0.01116 -0.0515 0.9491 0.3290
-0.500 0.1609 0.01980 0.01073 -0.0555 0.9392 1.0000
-0.250 0.2040 0.01990 0.01042 -0.0582 0.9247 1.0000
0.000 0.2448 0.01997 0.01020 -0.0605 0.9106 1.0000
0.250 0.2843 0.02001 0.01001 -0.0624 0.8971 1.0000
0.500 0.3235 0.02003 0.00985 -0.0643 0.8838 1.0000
0.750 0.3617 0.02001 0.00970 -0.0658 0.8701 1.0000
1.000 0.3969 0.01998 0.00957 -0.0667 0.8551 1.0000
1.250 0.4302 0.01993 0.00944 -0.0672 0.8388 1.0000
1.500 0.4629 0.01986 0.00931 -0.0674 0.8216 1.0000
1.750 0.4958 0.01974 0.00913 -0.0675 0.8035 1.0000
2.000 0.5269 0.01963 0.00899 -0.0673 0.7836 1.0000
2.250 0.5563 0.01955 0.00887 -0.0667 0.7612 1.0000
2.500 0.5872 0.01945 0.00872 -0.0663 0.7379 1.0000
2.750 0.6168 0.01940 0.00862 -0.0656 0.7118 1.0000
3.000 0.6441 0.01944 0.00860 -0.0647 0.6826 1.0000
3.250 0.6706 0.01954 0.00863 -0.0636 0.6510 1.0000
3.500 0.6955 0.01973 0.00872 -0.0623 0.6169 1.0000
3.750 0.7194 0.01998 0.00887 -0.0610 0.5813 1.0000
4.000 0.7432 0.02030 0.00904 -0.0597 0.5469 1.0000
4.250 0.7667 0.02071 0.00931 -0.0584 0.5152 1.0000
4.500 0.7899 0.02119 0.00965 -0.0573 0.4867 1.0000
4.750 0.8130 0.02175 0.01008 -0.0562 0.4619 1.0000
5.000 0.8366 0.02236 0.01061 -0.0553 0.4407 1.0000
5.250 0.8606 0.02301 0.01118 -0.0545 0.4217 1.0000
5.500 0.8848 0.02368 0.01186 -0.0538 0.4043 1.0000
5.750 0.9093 0.02439 0.01258 -0.0532 0.3887 1.0000
6.000 0.9337 0.02512 0.01336 -0.0526 0.3744 1.0000
6.250 0.9584 0.02587 0.01414 -0.0520 0.3614 1.0000
6.500 0.9824 0.02664 0.01503 -0.0514 0.3488 1.0000
6.750 1.0058 0.02746 0.01601 -0.0507 0.3366 1.0000
7.000 1.0290 0.02830 0.01700 -0.0499 0.3250 1.0000
7.250 1.0520 0.02915 0.01794 -0.0491 0.3137 1.0000
7.500 1.0738 0.02994 0.01881 -0.0481 0.3011 1.0000
7.750 1.0930 0.03069 0.01970 -0.0468 0.2870 1.0000
8.000 1.1107 0.03143 0.02062 -0.0453 0.2724 1.0000
8.250 1.1276 0.03219 0.02156 -0.0437 0.2580 1.0000
8.500 1.1440 0.03300 0.02256 -0.0420 0.2439 1.0000
8.750 1.1596 0.03387 0.02363 -0.0403 0.2300 1.0000
9.000 1.1736 0.03474 0.02469 -0.0384 0.2153 1.0000
9.250 1.1862 0.03568 0.02584 -0.0364 0.2002 1.0000
9.500 1.1963 0.03665 0.02693 -0.0341 0.1844 1.0000
9.750 1.2038 0.03782 0.02824 -0.0316 0.1678 1.0000
10.000 1.2071 0.03909 0.02968 -0.0289 0.1497 1.0000
10.250 1.2071 0.04042 0.03109 -0.0259 0.1327 1.0000
10.500 1.2041 0.04195 0.03262 -0.0228 0.1175 1.0000
10.750 1.2012 0.04389 0.03459 -0.0203 0.1049 1.0000
11.000 1.1973 0.04623 0.03697 -0.0181 0.0945 1.0000
11.250 1.1914 0.04889 0.03961 -0.0164 0.0867 1.0000
11.500 1.1857 0.05188 0.04270 -0.0150 0.0797 1.0000
11.750 1.1785 0.05521 0.04613 -0.0142 0.0742 1.0000
12.000 1.1714 0.05885 0.04994 -0.0137 0.0690 1.0000
12.250 1.1639 0.06254 0.05365 -0.0138 0.0654 1.0000
12.500 1.1573 0.06667 0.05796 -0.0140 0.0623 1.0000
12.750 1.1494 0.07123 0.06278 -0.0148 0.0597 1.0000
13.000 1.1402 0.07604 0.06778 -0.0160 0.0572 1.0000
13.250 1.1322 0.08080 0.07267 -0.0175 0.0552 1.0000
13.500 1.1272 0.08502 0.07688 -0.0186 0.0530 1.0000
13.750 1.1167 0.09072 0.08276 -0.0208 0.0518 1.0000
14.000 1.1005 0.09790 0.09021 -0.0244 0.0511 1.0000
14.250 1.0837 0.10557 0.09813 -0.0284 0.0509 1.0000
14.500 1.0627 0.11465 0.10742 -0.0335 0.0508 1.0000
14.750 1.0400 0.12474 0.11766 -0.0392 0.0512 1.0000
15.000 1.0163 0.13587 0.12884 -0.0455 0.0517 1.0000
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Polar data table (+)
Polar graphs
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