GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Reynolds number: 50,000 Max Cl/Cd: 37.76 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe325-il-50000-n5.txt Download as CSV file: xf-goe325-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 325 (PFALZ 54) 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3266 0.09685 0.09054 -0.0239 1.0000 0.0894
-7.000 -0.3269 0.09446 0.08824 -0.0245 1.0000 0.0922
-6.750 -0.3293 0.09265 0.08652 -0.0271 1.0000 0.0955
-6.500 -0.3293 0.09133 0.08523 -0.0331 1.0000 0.0970
-6.250 -0.3245 0.08655 0.08057 -0.0285 1.0000 0.0997
-6.000 -0.3197 0.08363 0.07770 -0.0269 1.0000 0.1048
-5.750 -0.3124 0.08187 0.07589 -0.0338 1.0000 0.1113
-5.500 -0.3074 0.07793 0.07204 -0.0323 1.0000 0.1136
-5.250 -0.3012 0.07480 0.06896 -0.0305 1.0000 0.1173
-5.000 -0.2814 0.07273 0.06668 -0.0389 1.0000 0.1264
-4.500 -0.2647 0.06596 0.05999 -0.0362 1.0000 0.1387
-4.250 -0.2549 0.06288 0.05696 -0.0357 1.0000 0.1481
-4.000 -0.2410 0.06011 0.05415 -0.0367 1.0000 0.1627
-3.750 -0.2245 0.05729 0.05129 -0.0381 0.9997 0.1772
-3.500 -0.1393 0.04853 0.04136 -0.0536 0.9930 0.0809
-3.250 -0.0899 0.04464 0.03692 -0.0600 0.9849 0.0817
-3.000 -0.0466 0.04099 0.03297 -0.0647 0.9766 0.0793
-2.750 -0.0011 0.03782 0.02935 -0.0693 0.9671 0.0776
-2.500 0.0451 0.03529 0.02626 -0.0735 0.9565 0.0797
-2.250 0.0914 0.03316 0.02347 -0.0773 0.9451 0.0817
-2.000 0.1365 0.03108 0.02096 -0.0806 0.9326 0.0814
-1.750 0.1806 0.02930 0.01877 -0.0834 0.9184 0.0816
-1.500 0.2222 0.02781 0.01688 -0.0855 0.9020 0.0823
-1.250 0.2601 0.02638 0.01525 -0.0869 0.8841 0.0837
-1.000 0.2966 0.02520 0.01397 -0.0880 0.8659 0.0881
-0.750 0.3295 0.02440 0.01292 -0.0881 0.8439 0.0954
-0.500 0.3649 0.02342 0.01178 -0.0885 0.8237 0.1000
-0.250 0.3973 0.02263 0.01086 -0.0886 0.8002 0.1050
0.000 0.4313 0.02191 0.00991 -0.0887 0.7779 0.1123
0.250 0.4630 0.02128 0.00917 -0.0887 0.7535 0.1248
0.500 0.4940 0.02061 0.00855 -0.0887 0.7296 0.1606
0.750 0.5197 0.01825 0.00805 -0.0874 0.7068 1.0000
1.000 0.5475 0.01844 0.00778 -0.0867 0.6826 1.0000
1.250 0.5748 0.01867 0.00763 -0.0860 0.6604 1.0000
1.500 0.6010 0.01896 0.00762 -0.0854 0.6381 1.0000
1.750 0.6272 0.01927 0.00764 -0.0847 0.6181 1.0000
2.000 0.6533 0.01960 0.00771 -0.0841 0.6000 1.0000
2.250 0.6796 0.01998 0.00789 -0.0837 0.5823 1.0000
2.500 0.7060 0.02038 0.00809 -0.0833 0.5659 1.0000
2.750 0.7324 0.02081 0.00836 -0.0829 0.5508 1.0000
3.000 0.7589 0.02127 0.00869 -0.0826 0.5367 1.0000
3.250 0.7855 0.02175 0.00905 -0.0823 0.5234 1.0000
3.500 0.8123 0.02225 0.00944 -0.0821 0.5111 1.0000
3.750 0.8384 0.02277 0.00995 -0.0819 0.4989 1.0000
4.000 0.8643 0.02332 0.01050 -0.0816 0.4873 1.0000
4.250 0.8903 0.02388 0.01105 -0.0814 0.4769 1.0000
4.500 0.9167 0.02442 0.01160 -0.0811 0.4677 1.0000
4.750 0.9417 0.02504 0.01232 -0.0809 0.4576 1.0000
5.000 0.9674 0.02564 0.01295 -0.0806 0.4492 1.0000
5.500 1.0175 0.02695 0.01449 -0.0800 0.4330 1.0000
5.750 1.0426 0.02762 0.01526 -0.0797 0.4258 1.0000
6.000 1.0670 0.02836 0.01615 -0.0794 0.4188 1.0000
6.250 1.0913 0.02909 0.01707 -0.0790 0.4119 1.0000
6.500 1.1159 0.02986 0.01798 -0.0786 0.4060 1.0000
6.750 1.1388 0.03078 0.01915 -0.0782 0.3996 1.0000
7.000 1.1641 0.03151 0.02000 -0.0779 0.3946 1.0000
7.250 1.1850 0.03261 0.02146 -0.0773 0.3881 1.0000
7.500 1.2081 0.03353 0.02260 -0.0768 0.3826 1.0000
7.750 1.2321 0.03445 0.02373 -0.0764 0.3781 1.0000
8.000 1.2503 0.03583 0.02551 -0.0756 0.3719 1.0000
8.250 1.2734 0.03675 0.02668 -0.0750 0.3668 1.0000
8.500 1.2908 0.03764 0.02793 -0.0737 0.3569 1.0000
8.750 1.3106 0.03715 0.02753 -0.0718 0.3392 1.0000
9.000 1.3289 0.03681 0.02729 -0.0698 0.3218 1.0000
9.250 1.3436 0.03694 0.02761 -0.0677 0.3055 1.0000
9.500 1.3473 0.03719 0.02813 -0.0644 0.2801 1.0000
9.750 1.3454 0.03764 0.02869 -0.0608 0.2453 1.0000
10.000 1.3425 0.03898 0.03020 -0.0576 0.1999 1.0000
10.500 1.3063 0.04515 0.03541 -0.0509 0.0913 1.0000
10.750 1.2879 0.04955 0.03974 -0.0494 0.0765 1.0000
11.000 1.2708 0.05439 0.04464 -0.0492 0.0686 1.0000
11.250 1.2537 0.05979 0.05017 -0.0500 0.0638 1.0000
11.500 1.2367 0.06567 0.05615 -0.0516 0.0609 1.0000
11.750 1.2223 0.07148 0.06221 -0.0533 0.0578 1.0000
12.000 1.2080 0.07734 0.06821 -0.0551 0.0553 1.0000
12.250 1.1945 0.08308 0.07407 -0.0567 0.0532 1.0000
12.500 1.1817 0.08865 0.07972 -0.0583 0.0512 1.0000
12.750 1.1699 0.09401 0.08510 -0.0596 0.0494 1.0000
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Polar data table (+)
Polar graphs
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