GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 505 AIRFOIL (goe505-il) Reynolds number: 50,000 Max Cl/Cd: 29.83 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe505-il-50000-n5.txt Download as CSV file: xf-goe505-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 505 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2913 0.10938 0.10305 -0.0466 0.9662 0.0832
-7.750 -0.2916 0.10609 0.09977 -0.0486 0.9614 0.0828
-7.500 -0.2953 0.10302 0.09672 -0.0499 0.9561 0.0823
-7.250 -0.3041 0.10014 0.09388 -0.0503 0.9496 0.0817
-7.000 -0.3028 0.09637 0.09009 -0.0531 0.9446 0.0812
-6.750 -0.3108 0.09318 0.08691 -0.0530 0.9374 0.0807
-6.500 -0.3093 0.08886 0.08254 -0.0555 0.9314 0.0794
-6.250 -0.3119 0.08463 0.07825 -0.0568 0.9248 0.0783
-6.000 -0.3117 0.07969 0.07320 -0.0588 0.9180 0.0771
-5.750 -0.3064 0.07370 0.06698 -0.0619 0.9125 0.0760
-5.500 -0.3071 0.06824 0.06127 -0.0624 0.9052 0.0753
-5.250 -0.2913 0.06428 0.05707 -0.0639 0.9003 0.0758
-5.000 -0.2812 0.06232 0.05500 -0.0628 0.8938 0.0772
-4.750 -0.2654 0.05952 0.05197 -0.0630 0.8879 0.0788
-4.500 -0.2455 0.05591 0.04797 -0.0641 0.8833 0.0806
-4.250 -0.2364 0.05282 0.04450 -0.0626 0.8758 0.0813
-4.000 -0.2136 0.04932 0.04043 -0.0631 0.8710 0.0826
-3.750 -0.1971 0.04683 0.03743 -0.0620 0.8644 0.0838
-3.500 -0.1738 0.04446 0.03446 -0.0616 0.8584 0.0859
-3.250 -0.1407 0.04296 0.03265 -0.0628 0.8540 0.0892
-3.000 -0.1257 0.04239 0.03200 -0.0609 0.8446 0.0927
-2.750 -0.0896 0.04108 0.03026 -0.0622 0.8395 0.0997
-2.500 -0.0698 0.04034 0.02943 -0.0609 0.8298 0.1043
-2.250 -0.0279 0.03920 0.02801 -0.0629 0.8236 0.1145
-2.000 -0.0043 0.03865 0.02747 -0.0621 0.8120 0.1250
-1.750 0.0346 0.03801 0.02670 -0.0635 0.8036 0.1471
-1.500 0.0648 0.03772 0.02641 -0.0637 0.7931 0.1687
-1.250 0.0861 0.03774 0.02638 -0.0624 0.7817 0.1957
-1.000 0.1231 0.03737 0.02592 -0.0634 0.7746 0.2262
-0.750 0.1452 0.03718 0.02566 -0.0624 0.7625 0.2425
-0.500 0.1908 0.03642 0.02477 -0.0649 0.7571 0.2639
-0.250 0.2108 0.03631 0.02458 -0.0635 0.7441 0.2793
0.000 0.2350 0.03609 0.02431 -0.0628 0.7324 0.2958
0.250 0.2748 0.03534 0.02355 -0.0642 0.7257 0.3175
0.500 0.2947 0.03519 0.02339 -0.0627 0.7125 0.3355
0.750 0.3174 0.03491 0.02311 -0.0617 0.6998 0.3558
1.000 0.3442 0.03442 0.02263 -0.0611 0.6887 0.3800
1.250 0.3762 0.03353 0.02182 -0.0611 0.6799 0.4111
1.500 0.3965 0.03301 0.02147 -0.0596 0.6666 0.4454
2.000 0.5356 0.03101 0.02047 -0.0745 0.6442 1.0000
2.250 0.5651 0.03057 0.01981 -0.0739 0.6328 1.0000
2.500 0.5885 0.03041 0.01946 -0.0726 0.6184 1.0000
2.750 0.6137 0.03021 0.01908 -0.0716 0.6041 1.0000
3.000 0.6404 0.03001 0.01869 -0.0708 0.5901 1.0000
3.250 0.6688 0.02980 0.01828 -0.0703 0.5765 1.0000
3.500 0.6991 0.02958 0.01786 -0.0700 0.5635 1.0000
3.750 0.7312 0.02935 0.01741 -0.0701 0.5508 1.0000
4.000 0.7549 0.02953 0.01743 -0.0692 0.5368 1.0000
4.250 0.7775 0.02980 0.01755 -0.0682 0.5236 1.0000
4.500 0.8019 0.03006 0.01766 -0.0675 0.5120 1.0000
4.750 0.8328 0.03014 0.01754 -0.0677 0.5020 1.0000
5.000 0.8498 0.03073 0.01807 -0.0661 0.4908 1.0000
5.250 0.8739 0.03112 0.01835 -0.0655 0.4815 1.0000
5.500 0.8976 0.03155 0.01868 -0.0649 0.4724 1.0000
5.750 0.9181 0.03212 0.01921 -0.0639 0.4639 1.0000
6.000 0.9428 0.03258 0.01960 -0.0635 0.4562 1.0000
6.250 0.9635 0.03320 0.02018 -0.0626 0.4488 1.0000
6.500 0.9844 0.03380 0.02076 -0.0617 0.4412 1.0000
6.750 1.0089 0.03433 0.02125 -0.0613 0.4343 1.0000
7.000 1.0232 0.03515 0.02212 -0.0596 0.4271 1.0000
7.250 1.0567 0.03543 0.02229 -0.0605 0.4206 1.0000
7.500 1.0596 0.03659 0.02359 -0.0572 0.4133 1.0000
7.750 1.0848 0.03705 0.02400 -0.0570 0.4066 1.0000
8.000 1.0958 0.03804 0.02506 -0.0549 0.4001 1.0000
8.250 1.1088 0.03894 0.02602 -0.0531 0.3935 1.0000
8.500 1.1411 0.03926 0.02629 -0.0538 0.3879 1.0000
8.750 1.1351 0.04088 0.02810 -0.0498 0.3816 1.0000
9.000 1.1517 0.04172 0.02899 -0.0486 0.3758 1.0000
9.250 1.1794 0.04224 0.02949 -0.0487 0.3709 1.0000
9.500 1.1677 0.04428 0.03177 -0.0444 0.3652 1.0000
9.750 1.1794 0.04544 0.03301 -0.0428 0.3600 1.0000
10.000 1.2144 0.04563 0.03318 -0.0437 0.3556 1.0000
10.250 1.1903 0.04852 0.03633 -0.0387 0.3503 1.0000
10.500 1.1839 0.05081 0.03877 -0.0358 0.3452 1.0000
10.750 1.2062 0.05152 0.03954 -0.0353 0.3410 1.0000
11.000 1.2117 0.05324 0.04139 -0.0336 0.3367 1.0000
11.250 1.1476 0.05987 0.04827 -0.0278 0.3299 1.0000
11.500 1.1563 0.06150 0.05001 -0.0266 0.3254 1.0000
11.750 1.2006 0.06042 0.04896 -0.0272 0.3224 1.0000
12.000 1.0332 0.07990 0.06867 -0.0231 0.3084 1.0000
12.250 1.0621 0.07934 0.06818 -0.0222 0.3063 1.0000
12.750 0.9654 0.10026 0.08925 -0.0253 0.2887 1.0000
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Polar data table (+)
Polar graphs
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