GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Reynolds number: 500,000 Max Cl/Cd: 100.08 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe326-il-500000-n5.txt Download as CSV file: xf-goe326-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3478 0.09610 0.09393 -0.0211 1.0000 0.0090
-8.500 -0.3440 0.09250 0.09036 -0.0229 1.0000 0.0091
-8.250 -0.3411 0.08890 0.08678 -0.0246 1.0000 0.0092
-8.000 -0.3309 0.08415 0.08203 -0.0295 0.9687 0.0095
-7.500 -0.3107 0.07150 0.06927 -0.0441 0.9129 0.0106
-7.250 -0.2943 0.06900 0.06670 -0.0471 0.8980 0.0109
-7.000 -0.2766 0.06634 0.06397 -0.0504 0.8847 0.0113
-6.750 -0.2578 0.06278 0.06034 -0.0547 0.8720 0.0119
-6.500 -0.2369 0.05731 0.05476 -0.0612 0.8594 0.0126
-6.250 -0.2109 0.04697 0.04416 -0.0723 0.8473 0.0142
-6.000 -0.1869 0.04539 0.04248 -0.0738 0.8344 0.0147
-5.500 -0.1308 0.03053 0.02685 -0.0838 0.8099 0.0188
-5.250 -0.1055 0.03010 0.02632 -0.0840 0.7976 0.0193
-5.000 -0.0798 0.02930 0.02540 -0.0843 0.7866 0.0201
-4.750 -0.0533 0.02686 0.02270 -0.0851 0.7763 0.0213
-4.500 -0.0252 0.02030 0.01535 -0.0860 0.7682 0.0245
-4.250 0.0003 0.01811 0.01279 -0.0864 0.7594 0.0255
-4.000 0.0274 0.01755 0.01210 -0.0864 0.7503 0.0261
-3.750 0.0546 0.01712 0.01154 -0.0864 0.7419 0.0270
-3.500 0.0819 0.01630 0.01053 -0.0864 0.7331 0.0278
-3.250 0.1095 0.01521 0.00918 -0.0864 0.7248 0.0284
-3.000 0.1371 0.01425 0.00797 -0.0863 0.7159 0.0290
-2.750 0.1650 0.01346 0.00699 -0.0863 0.7073 0.0297
-2.500 0.1927 0.01291 0.00628 -0.0862 0.6987 0.0306
-2.250 0.2207 0.01229 0.00552 -0.0861 0.6894 0.0311
-2.000 0.2486 0.01181 0.00492 -0.0860 0.6798 0.0316
-1.750 0.2764 0.01145 0.00444 -0.0859 0.6691 0.0320
-1.500 0.3043 0.01115 0.00406 -0.0858 0.6562 0.0324
-1.250 0.3320 0.01090 0.00373 -0.0857 0.6410 0.0326
-1.000 0.3593 0.01037 0.00309 -0.0856 0.6218 0.0334
-0.750 0.3864 0.01011 0.00271 -0.0854 0.5960 0.0340
-0.500 0.4134 0.00999 0.00246 -0.0852 0.5700 0.0347
-0.250 0.4405 0.00996 0.00232 -0.0851 0.5489 0.0358
0.000 0.4679 0.00993 0.00222 -0.0850 0.5328 0.0369
0.250 0.4953 0.00989 0.00211 -0.0849 0.5197 0.0377
0.500 0.5229 0.00986 0.00202 -0.0848 0.5082 0.0389
0.750 0.5506 0.00984 0.00196 -0.0847 0.4974 0.0405
1.000 0.5781 0.00986 0.00192 -0.0847 0.4853 0.0422
1.250 0.6057 0.00989 0.00190 -0.0846 0.4738 0.0443
1.500 0.6333 0.00990 0.00188 -0.0846 0.4631 0.0494
1.750 0.6610 0.00993 0.00190 -0.0845 0.4534 0.0552
2.000 0.6886 0.00997 0.00194 -0.0845 0.4426 0.0682
2.500 0.7405 0.00822 0.00222 -0.0843 0.4203 1.0000
2.750 0.7678 0.00836 0.00230 -0.0842 0.4104 1.0000
3.000 0.7950 0.00852 0.00238 -0.0840 0.3993 1.0000
3.250 0.8219 0.00870 0.00249 -0.0839 0.3858 1.0000
3.500 0.8488 0.00888 0.00261 -0.0838 0.3733 1.0000
3.750 0.8758 0.00906 0.00273 -0.0836 0.3622 1.0000
4.000 0.9026 0.00924 0.00287 -0.0835 0.3522 1.0000
4.250 0.9293 0.00945 0.00304 -0.0834 0.3418 1.0000
4.500 0.9558 0.00966 0.00320 -0.0832 0.3301 1.0000
4.750 0.9823 0.00987 0.00338 -0.0830 0.3191 1.0000
5.000 1.0087 0.01009 0.00358 -0.0829 0.3090 1.0000
5.250 1.0348 0.01034 0.00380 -0.0826 0.2974 1.0000
5.500 1.0606 0.01061 0.00402 -0.0824 0.2843 1.0000
5.750 1.0855 0.01098 0.00430 -0.0821 0.2591 1.0000
6.000 1.1095 0.01146 0.00462 -0.0816 0.2284 1.0000
6.250 1.1320 0.01210 0.00503 -0.0810 0.1865 1.0000
6.500 1.1509 0.01318 0.00572 -0.0800 0.1240 1.0000
6.750 1.1741 0.01371 0.00619 -0.0795 0.1089 1.0000
7.000 1.1975 0.01419 0.00663 -0.0789 0.0986 1.0000
7.250 1.2211 0.01463 0.00705 -0.0784 0.0871 1.0000
7.500 1.2426 0.01529 0.00756 -0.0777 0.0636 1.0000
7.750 1.2573 0.01667 0.00865 -0.0761 0.0183 1.0000
8.000 1.2786 0.01728 0.00930 -0.0752 0.0144 1.0000
8.250 1.3006 0.01779 0.00988 -0.0744 0.0128 1.0000
8.500 1.3217 0.01835 0.01053 -0.0735 0.0115 1.0000
8.750 1.3414 0.01903 0.01128 -0.0725 0.0104 1.0000
9.000 1.3593 0.01983 0.01220 -0.0712 0.0096 1.0000
9.250 1.3785 0.02046 0.01291 -0.0701 0.0091 1.0000
9.500 1.3964 0.02116 0.01369 -0.0688 0.0085 1.0000
9.750 1.4131 0.02190 0.01450 -0.0674 0.0079 1.0000
10.000 1.4280 0.02272 0.01538 -0.0658 0.0074 1.0000
10.250 1.4374 0.02373 0.01647 -0.0633 0.0070 1.0000
10.500 1.4431 0.02498 0.01782 -0.0605 0.0067 1.0000
10.750 1.4523 0.02605 0.01900 -0.0584 0.0065 1.0000
11.000 1.4600 0.02730 0.02036 -0.0564 0.0063 1.0000
11.250 1.4662 0.02874 0.02191 -0.0545 0.0061 1.0000
11.500 1.4711 0.03038 0.02365 -0.0527 0.0059 1.0000
11.750 1.4751 0.03219 0.02558 -0.0512 0.0058 1.0000
12.000 1.4783 0.03419 0.02769 -0.0499 0.0056 1.0000
12.250 1.4810 0.03636 0.02995 -0.0488 0.0054 1.0000
12.500 1.4835 0.03866 0.03235 -0.0481 0.0053 1.0000
12.750 1.4847 0.04121 0.03500 -0.0475 0.0051 1.0000
13.000 1.4840 0.04406 0.03796 -0.0471 0.0050 1.0000
13.250 1.4801 0.04740 0.04142 -0.0469 0.0049 1.0000
13.500 1.4718 0.05136 0.04551 -0.0469 0.0047 1.0000
13.750 1.4653 0.05529 0.04955 -0.0472 0.0047 1.0000
14.000 1.4615 0.05899 0.05339 -0.0476 0.0046 1.0000
14.250 1.4558 0.06305 0.05758 -0.0482 0.0045 1.0000
14.500 1.4491 0.06742 0.06207 -0.0491 0.0045 1.0000
14.750 1.4417 0.07197 0.06675 -0.0501 0.0044 1.0000
15.000 1.4339 0.07664 0.07155 -0.0512 0.0043 1.0000
15.250 1.4257 0.08146 0.07649 -0.0524 0.0043 1.0000
15.500 1.4175 0.08637 0.08152 -0.0538 0.0042 1.0000
15.750 1.4091 0.09134 0.08661 -0.0552 0.0042 1.0000
16.000 1.4006 0.09640 0.09179 -0.0568 0.0041 1.0000
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Polar data table (+)
Polar graphs
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