GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.65 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe326-il-1000000-n5.txt Download as CSV file: xf-goe326-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 326 (PFALZ 55) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3707 0.09199 0.09037 -0.0237 0.9366 0.0061
-8.750 -0.3672 0.08887 0.08714 -0.0249 0.9068 0.0064
-7.750 -0.3911 0.01513 0.01100 -0.0867 0.8463 0.0138
-7.500 -0.3639 0.01497 0.01079 -0.0865 0.8340 0.0148
-6.750 -0.2819 0.01453 0.01012 -0.0861 0.7924 0.0178
-6.500 -0.2557 0.01361 0.00895 -0.0860 0.7782 0.0185
-6.250 -0.2284 0.01328 0.00848 -0.0859 0.7664 0.0190
-6.000 -0.2001 0.01359 0.00879 -0.0858 0.7560 0.0195
-5.500 -0.1435 0.01431 0.00952 -0.0857 0.7372 0.0202
-5.000 -0.0877 0.01415 0.00923 -0.0857 0.7237 0.0214
-4.750 -0.0602 0.01358 0.00851 -0.0857 0.7172 0.0223
-4.500 -0.0324 0.01309 0.00789 -0.0857 0.7109 0.0231
-4.250 -0.0047 0.01254 0.00721 -0.0857 0.7038 0.0236
-4.000 0.0232 0.01220 0.00675 -0.0857 0.6968 0.0240
-3.750 0.0512 0.01177 0.00621 -0.0857 0.6886 0.0242
-3.500 0.0791 0.01133 0.00566 -0.0857 0.6809 0.0244
-3.250 0.1072 0.01096 0.00517 -0.0857 0.6721 0.0245
-3.000 0.1346 0.00992 0.00395 -0.0857 0.6634 0.0254
-2.750 0.1626 0.00956 0.00352 -0.0857 0.6522 0.0261
-2.500 0.1906 0.00934 0.00322 -0.0856 0.6380 0.0266
-2.250 0.2185 0.00916 0.00296 -0.0856 0.6171 0.0271
-2.000 0.2460 0.00909 0.00275 -0.0855 0.5858 0.0276
-1.750 0.2734 0.00904 0.00256 -0.0854 0.5563 0.0281
-1.500 0.3011 0.00898 0.00238 -0.0853 0.5365 0.0286
-1.250 0.3289 0.00890 0.00222 -0.0853 0.5216 0.0290
-1.000 0.3569 0.00881 0.00206 -0.0853 0.5096 0.0295
-0.750 0.3849 0.00872 0.00192 -0.0853 0.4994 0.0298
-0.500 0.4129 0.00866 0.00179 -0.0853 0.4900 0.0302
-0.250 0.4411 0.00859 0.00168 -0.0853 0.4809 0.0306
0.000 0.4692 0.00855 0.00160 -0.0853 0.4704 0.0310
0.250 0.4971 0.00855 0.00155 -0.0853 0.4589 0.0316
0.500 0.5252 0.00856 0.00151 -0.0853 0.4477 0.0322
0.750 0.5533 0.00855 0.00147 -0.0854 0.4385 0.0325
1.000 0.5813 0.00853 0.00140 -0.0854 0.4279 0.0345
1.250 0.6092 0.00856 0.00140 -0.0854 0.4156 0.0375
1.500 0.6371 0.00860 0.00142 -0.0854 0.4040 0.0405
1.750 0.6650 0.00865 0.00144 -0.0854 0.3942 0.0431
2.000 0.6927 0.00871 0.00149 -0.0854 0.3834 0.0507
2.250 0.7204 0.00879 0.00154 -0.0854 0.3715 0.0598
2.500 0.7480 0.00873 0.00165 -0.0855 0.3596 0.1570
3.000 0.7992 0.00728 0.00198 -0.0851 0.3365 1.0000
3.250 0.8265 0.00744 0.00208 -0.0851 0.3268 1.0000
3.500 0.8539 0.00759 0.00218 -0.0850 0.3173 1.0000
3.750 0.8811 0.00776 0.00229 -0.0849 0.3065 1.0000
4.000 0.9082 0.00794 0.00242 -0.0849 0.2958 1.0000
4.250 0.9353 0.00811 0.00255 -0.0848 0.2864 1.0000
4.500 0.9624 0.00828 0.00269 -0.0847 0.2775 1.0000
4.750 0.9892 0.00848 0.00285 -0.0846 0.2667 1.0000
5.000 1.0154 0.00876 0.00303 -0.0844 0.2480 1.0000
5.250 1.0402 0.00921 0.00330 -0.0841 0.2147 1.0000
5.500 1.0616 0.01008 0.00379 -0.0834 0.1465 1.0000
5.750 1.0848 0.01071 0.00423 -0.0828 0.1136 1.0000
6.000 1.1103 0.01102 0.00450 -0.0826 0.1046 1.0000
6.250 1.1360 0.01130 0.00476 -0.0823 0.0973 1.0000
6.500 1.1610 0.01165 0.00506 -0.0820 0.0871 1.0000
6.750 1.1852 0.01209 0.00540 -0.0816 0.0701 1.0000
7.000 1.2037 0.01321 0.00621 -0.0804 0.0208 1.0000
7.250 1.2275 0.01366 0.00665 -0.0799 0.0143 1.0000
7.500 1.2519 0.01401 0.00702 -0.0795 0.0124 1.0000
7.750 1.2757 0.01442 0.00747 -0.0790 0.0106 1.0000
8.000 1.2992 0.01484 0.00792 -0.0784 0.0094 1.0000
8.250 1.3228 0.01522 0.00834 -0.0779 0.0087 1.0000
8.500 1.3457 0.01566 0.00880 -0.0773 0.0079 1.0000
8.750 1.3676 0.01617 0.00933 -0.0766 0.0071 1.0000
9.000 1.3894 0.01667 0.00988 -0.0758 0.0066 1.0000
9.250 1.4111 0.01715 0.01040 -0.0751 0.0062 1.0000
9.500 1.4322 0.01766 0.01095 -0.0742 0.0058 1.0000
9.750 1.4526 0.01820 0.01153 -0.0733 0.0055 1.0000
10.000 1.4718 0.01880 0.01217 -0.0722 0.0051 1.0000
10.250 1.4890 0.01954 0.01298 -0.0709 0.0048 1.0000
10.500 1.5059 0.02024 0.01375 -0.0695 0.0046 1.0000
10.750 1.5228 0.02088 0.01444 -0.0681 0.0044 1.0000
11.000 1.5372 0.02156 0.01518 -0.0663 0.0042 1.0000
11.250 1.5489 0.02231 0.01599 -0.0642 0.0040 1.0000
11.500 1.5602 0.02312 0.01686 -0.0621 0.0039 1.0000
11.750 1.5706 0.02404 0.01785 -0.0601 0.0037 1.0000
12.000 1.5802 0.02507 0.01895 -0.0582 0.0036 1.0000
12.250 1.5886 0.02625 0.02021 -0.0564 0.0035 1.0000
12.500 1.5955 0.02762 0.02166 -0.0547 0.0033 1.0000
12.750 1.5996 0.02932 0.02345 -0.0530 0.0032 1.0000
13.000 1.5999 0.03146 0.02570 -0.0513 0.0031 1.0000
13.250 1.6049 0.03331 0.02764 -0.0502 0.0031 1.0000
13.500 1.6081 0.03541 0.02984 -0.0492 0.0030 1.0000
13.750 1.6099 0.03778 0.03232 -0.0485 0.0030 1.0000
14.000 1.6107 0.04034 0.03499 -0.0479 0.0029 1.0000
14.250 1.6096 0.04321 0.03796 -0.0475 0.0029 1.0000
14.500 1.6070 0.04636 0.04123 -0.0473 0.0028 1.0000
14.750 1.6026 0.04980 0.04478 -0.0473 0.0028 1.0000
15.000 1.5973 0.05350 0.04860 -0.0475 0.0028 1.0000
15.250 1.5899 0.05764 0.05287 -0.0480 0.0027 1.0000
15.500 1.5817 0.06208 0.05743 -0.0488 0.0027 1.0000
15.750 1.5731 0.06673 0.06220 -0.0499 0.0026 1.0000
16.000 1.5631 0.07172 0.06731 -0.0512 0.0026 1.0000
16.250 1.5509 0.07709 0.07280 -0.0526 0.0026 1.0000
16.500 1.5388 0.08256 0.07839 -0.0542 0.0026 1.0000
16.750 1.5255 0.08830 0.08424 -0.0560 0.0026 1.0000
17.000 1.5120 0.09413 0.09019 -0.0578 0.0025 1.0000
17.250 1.4977 0.10021 0.09639 -0.0599 0.0025 1.0000
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Polar data table (+)
Polar graphs
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