GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 389 AIRFOIL (goe389-il) Reynolds number: 100,000 Max Cl/Cd: 56.19 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe389-il-100000-n5.txt Download as CSV file: xf-goe389-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 389 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2615 0.09855 0.09396 -0.0370 1.0000 0.0651
-9.250 -0.2748 0.09570 0.09119 -0.0392 1.0000 0.0663
-8.250 -0.3799 0.08698 0.08234 -0.0401 1.0000 0.0433
-8.000 -0.3812 0.08419 0.07962 -0.0388 1.0000 0.0429
-7.750 -0.3856 0.08120 0.07670 -0.0386 1.0000 0.0425
-7.500 -0.3925 0.07815 0.07373 -0.0386 1.0000 0.0422
-7.250 -0.4004 0.07499 0.07063 -0.0386 1.0000 0.0419
-7.000 -0.4032 0.07067 0.06632 -0.0410 0.9987 0.0419
-6.750 -0.3758 0.05885 0.05415 -0.0566 0.9889 0.0431
-6.500 -0.3511 0.05035 0.04516 -0.0651 0.9807 0.0435
-6.250 -0.3249 0.04422 0.03863 -0.0705 0.9744 0.0441
-6.000 -0.2981 0.04290 0.03734 -0.0722 0.9675 0.0461
-5.750 -0.2669 0.03956 0.03368 -0.0757 0.9615 0.0483
-5.500 -0.2362 0.03511 0.02865 -0.0790 0.9538 0.0489
-5.250 -0.2017 0.03154 0.02447 -0.0820 0.9471 0.0497
-5.000 -0.1655 0.02897 0.02132 -0.0845 0.9393 0.0524
-4.750 -0.1296 0.02672 0.01852 -0.0864 0.9310 0.0536
-4.500 -0.0929 0.02482 0.01617 -0.0882 0.9229 0.0542
-4.250 -0.0597 0.02341 0.01437 -0.0891 0.9133 0.0549
-4.000 -0.0245 0.02191 0.01274 -0.0906 0.9066 0.0561
-3.750 0.0049 0.02096 0.01170 -0.0909 0.8968 0.0575
-3.500 0.0380 0.02021 0.01084 -0.0919 0.8898 0.0607
-3.250 0.0671 0.01955 0.01005 -0.0920 0.8799 0.0636
-3.000 0.0965 0.01885 0.00924 -0.0921 0.8703 0.0654
-2.750 0.1274 0.01817 0.00847 -0.0924 0.8620 0.0672
-2.500 0.1539 0.01755 0.00786 -0.0921 0.8507 0.0702
-2.250 0.1815 0.01707 0.00733 -0.0919 0.8398 0.0746
-2.000 0.2100 0.01660 0.00677 -0.0917 0.8292 0.0815
-1.750 0.2384 0.01608 0.00626 -0.0916 0.8186 0.0955
-1.500 0.2651 0.01551 0.00596 -0.0913 0.8063 0.1449
-1.250 0.2919 0.01491 0.00579 -0.0912 0.7941 0.2754
-1.000 0.3180 0.01421 0.00567 -0.0909 0.7820 0.4350
-0.750 0.3409 0.01289 0.00565 -0.0884 0.7707 0.8508
-0.500 0.3851 0.01275 0.00530 -0.0913 0.7573 1.0000
-0.250 0.4125 0.01280 0.00513 -0.0909 0.7437 1.0000
0.000 0.4394 0.01288 0.00500 -0.0904 0.7293 1.0000
0.250 0.4660 0.01298 0.00491 -0.0899 0.7143 1.0000
0.500 0.4924 0.01310 0.00486 -0.0894 0.6987 1.0000
0.750 0.5183 0.01323 0.00485 -0.0889 0.6818 1.0000
1.000 0.5439 0.01337 0.00486 -0.0883 0.6637 1.0000
1.250 0.5695 0.01351 0.00488 -0.0877 0.6448 1.0000
1.500 0.5952 0.01366 0.00490 -0.0871 0.6256 1.0000
1.750 0.6208 0.01381 0.00493 -0.0865 0.6057 1.0000
2.000 0.6464 0.01399 0.00497 -0.0860 0.5867 1.0000
2.250 0.6720 0.01419 0.00504 -0.0854 0.5695 1.0000
2.500 0.6977 0.01443 0.00513 -0.0849 0.5541 1.0000
2.750 0.7234 0.01468 0.00527 -0.0844 0.5402 1.0000
3.000 0.7492 0.01496 0.00546 -0.0840 0.5278 1.0000
3.250 0.7750 0.01526 0.00566 -0.0836 0.5169 1.0000
3.500 0.8008 0.01558 0.00590 -0.0832 0.5067 1.0000
3.750 0.8266 0.01589 0.00620 -0.0828 0.4966 1.0000
4.000 0.8521 0.01623 0.00648 -0.0824 0.4869 1.0000
4.250 0.8775 0.01658 0.00678 -0.0820 0.4766 1.0000
4.500 0.9028 0.01691 0.00714 -0.0816 0.4663 1.0000
4.750 0.9281 0.01727 0.00747 -0.0811 0.4573 1.0000
5.000 0.9533 0.01761 0.00784 -0.0807 0.4480 1.0000
5.250 0.9786 0.01798 0.00826 -0.0803 0.4402 1.0000
5.500 1.0038 0.01834 0.00867 -0.0799 0.4322 1.0000
5.750 1.0288 0.01871 0.00910 -0.0795 0.4244 1.0000
6.000 1.0536 0.01908 0.00954 -0.0790 0.4165 1.0000
6.250 1.0785 0.01947 0.01005 -0.0786 0.4093 1.0000
6.500 1.1028 0.01985 0.01052 -0.0780 0.4011 1.0000
6.750 1.1257 0.02019 0.01098 -0.0773 0.3896 1.0000
7.000 1.1462 0.02047 0.01131 -0.0760 0.3720 1.0000
7.250 1.1653 0.02075 0.01165 -0.0746 0.3497 1.0000
7.500 1.1850 0.02109 0.01206 -0.0734 0.3285 1.0000
7.750 1.2044 0.02151 0.01252 -0.0721 0.3067 1.0000
8.000 1.2239 0.02199 0.01306 -0.0709 0.2844 1.0000
8.250 1.2411 0.02261 0.01365 -0.0694 0.2547 1.0000
8.500 1.2515 0.02371 0.01447 -0.0671 0.1996 1.0000
8.750 1.2589 0.02519 0.01562 -0.0647 0.1501 1.0000
9.000 1.2673 0.02662 0.01690 -0.0624 0.1261 1.0000
9.250 1.2759 0.02797 0.01823 -0.0601 0.1078 1.0000
9.500 1.2787 0.02956 0.01969 -0.0571 0.0658 1.0000
9.750 1.2760 0.03156 0.02149 -0.0537 0.0447 1.0000
10.000 1.2763 0.03342 0.02335 -0.0510 0.0305 1.0000
10.250 1.2772 0.03532 0.02530 -0.0487 0.0266 1.0000
10.500 1.2779 0.03735 0.02741 -0.0466 0.0247 1.0000
10.750 1.2788 0.03949 0.02973 -0.0449 0.0236 1.0000
11.000 1.2786 0.04184 0.03225 -0.0434 0.0228 1.0000
11.250 1.2769 0.04449 0.03506 -0.0423 0.0220 1.0000
11.500 1.2735 0.04747 0.03821 -0.0415 0.0212 1.0000
11.750 1.2684 0.05080 0.04170 -0.0410 0.0206 1.0000
12.000 1.2611 0.05454 0.04559 -0.0408 0.0200 1.0000
12.250 1.2525 0.05862 0.04983 -0.0410 0.0195 1.0000
12.500 1.2444 0.06279 0.05414 -0.0414 0.0191 1.0000
12.750 1.2384 0.06683 0.05836 -0.0419 0.0188 1.0000
13.000 1.2322 0.07101 0.06271 -0.0426 0.0186 1.0000
13.250 1.2261 0.07525 0.06711 -0.0433 0.0183 1.0000
13.500 1.2206 0.07944 0.07146 -0.0441 0.0182 1.0000
13.750 1.2162 0.08353 0.07569 -0.0448 0.0180 1.0000
14.000 1.2128 0.08745 0.07974 -0.0455 0.0178 1.0000
14.250 1.2106 0.09117 0.08359 -0.0460 0.0176 1.0000
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Polar data table (+)
Polar graphs
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