GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Reynolds number: 50,000 Max Cl/Cd: 37.88 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe329-il-50000-n5.txt Download as CSV file: xf-goe329-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 329 (PFALZ 58) 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3182 0.10568 0.09960 -0.0253 1.0000 0.0994
-7.250 -0.3345 0.10524 0.09929 -0.0245 1.0000 0.1012
-7.000 -0.3499 0.10509 0.09923 -0.0261 1.0000 0.1024
-6.750 -0.3438 0.10140 0.09559 -0.0279 0.9971 0.1041
-6.500 -0.3240 0.09663 0.09082 -0.0266 0.9929 0.1085
-6.250 -0.2996 0.09285 0.08698 -0.0336 0.9846 0.1151
-6.000 -0.2720 0.08891 0.08293 -0.0450 0.9743 0.1199
-5.750 -0.2531 0.08470 0.07873 -0.0444 0.9673 0.1243
-5.250 -0.1989 0.07705 0.07095 -0.0558 0.9498 0.1403
-5.000 -0.1692 0.07358 0.06735 -0.0629 0.9398 0.1533
-4.000 -0.0508 0.06010 0.05353 -0.0789 0.9048 0.2175
-3.750 -0.0152 0.05675 0.05010 -0.0829 0.8990 0.2490
-3.500 0.0026 0.05427 0.04764 -0.0824 0.8876 0.2821
-3.000 0.1396 0.04531 0.03693 -0.1040 0.8709 0.1049
-2.750 0.1805 0.04278 0.03380 -0.1064 0.8614 0.0877
-2.500 0.2160 0.04009 0.03099 -0.1086 0.8530 0.0839
-2.250 0.2484 0.03810 0.02865 -0.1097 0.8415 0.0797
-2.000 0.2875 0.03628 0.02623 -0.1113 0.8321 0.0761
-1.750 0.3211 0.03466 0.02434 -0.1122 0.8216 0.0765
-1.500 0.3513 0.03336 0.02277 -0.1125 0.8090 0.0767
-1.250 0.3839 0.03232 0.02130 -0.1126 0.7972 0.0754
-1.000 0.4178 0.03101 0.01971 -0.1131 0.7869 0.0747
-0.750 0.4463 0.03000 0.01850 -0.1127 0.7734 0.0744
-0.500 0.4742 0.02914 0.01745 -0.1122 0.7594 0.0743
-0.250 0.5017 0.02836 0.01648 -0.1114 0.7454 0.0744
0.000 0.5298 0.02770 0.01562 -0.1107 0.7314 0.0753
0.250 0.5575 0.02696 0.01479 -0.1101 0.7173 0.0781
0.500 0.5849 0.02641 0.01412 -0.1094 0.7030 0.0812
0.750 0.6124 0.02594 0.01351 -0.1088 0.6889 0.0832
1.000 0.6400 0.02556 0.01296 -0.1082 0.6748 0.0853
1.250 0.6678 0.02525 0.01247 -0.1077 0.6608 0.0879
1.500 0.6953 0.02498 0.01211 -0.1073 0.6467 0.0920
1.750 0.7221 0.02486 0.01191 -0.1068 0.6324 0.1009
2.250 0.7687 0.02291 0.01184 -0.1047 0.6062 1.0000
2.500 0.7957 0.02319 0.01175 -0.1041 0.5940 1.0000
2.750 0.8235 0.02344 0.01170 -0.1037 0.5831 1.0000
3.000 0.8490 0.02385 0.01191 -0.1033 0.5710 1.0000
3.250 0.8746 0.02428 0.01217 -0.1029 0.5599 1.0000
3.500 0.9019 0.02463 0.01233 -0.1027 0.5505 1.0000
3.750 0.9270 0.02514 0.01276 -0.1024 0.5403 1.0000
4.000 0.9526 0.02564 0.01317 -0.1021 0.5311 1.0000
4.250 0.9789 0.02611 0.01354 -0.1019 0.5227 1.0000
4.500 1.0033 0.02672 0.01415 -0.1016 0.5140 1.0000
4.750 1.0298 0.02723 0.01460 -0.1014 0.5066 1.0000
5.000 1.0535 0.02791 0.01531 -0.1010 0.4987 1.0000
5.250 1.0791 0.02849 0.01590 -0.1008 0.4917 1.0000
5.500 1.1033 0.02920 0.01664 -0.1005 0.4849 1.0000
5.750 1.1267 0.02995 0.01746 -0.1001 0.4780 1.0000
6.000 1.1545 0.03048 0.01798 -0.1001 0.4729 1.0000
6.250 1.1733 0.03153 0.01923 -0.0993 0.4656 1.0000
6.500 1.1980 0.03224 0.02000 -0.0991 0.4600 1.0000
6.750 1.2216 0.03307 0.02092 -0.0987 0.4548 1.0000
7.000 1.2399 0.03422 0.02231 -0.0979 0.4487 1.0000
7.250 1.2642 0.03502 0.02320 -0.0976 0.4438 1.0000
7.500 1.2860 0.03600 0.02432 -0.0971 0.4389 1.0000
7.750 1.3006 0.03741 0.02602 -0.0959 0.4330 1.0000
8.000 1.3225 0.03839 0.02716 -0.0954 0.4285 1.0000
8.250 1.3482 0.03921 0.02810 -0.0953 0.4247 1.0000
8.500 1.3523 0.04131 0.03055 -0.0932 0.4187 1.0000
8.750 1.3687 0.04265 0.03213 -0.0922 0.4139 1.0000
9.000 1.3940 0.04350 0.03315 -0.0920 0.4104 1.0000
9.250 1.3924 0.04606 0.03604 -0.0894 0.4051 1.0000
9.500 1.3934 0.04842 0.03867 -0.0872 0.3998 1.0000
9.750 1.4133 0.04957 0.04004 -0.0865 0.3959 1.0000
10.000 1.4110 0.05213 0.04288 -0.0840 0.3907 1.0000
10.250 1.3606 0.05818 0.04906 -0.0787 0.3844 1.0000
10.500 1.4078 0.05556 0.04669 -0.0782 0.3743 1.0000
10.750 1.2550 0.07567 0.06664 -0.0761 0.3667 1.0000
11.000 1.2764 0.07639 0.06758 -0.0751 0.3638 1.0000
11.250 1.2027 0.09083 0.08194 -0.0784 0.3500 1.0000
11.500 1.2264 0.09099 0.08235 -0.0771 0.3474 1.0000
11.750 1.3188 0.07499 0.06676 -0.0691 0.3269 1.0000
12.000 1.2455 0.09351 0.08528 -0.0749 0.3306 1.0000
12.250 1.1703 0.10992 0.10151 -0.0804 0.3207 1.0000
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Polar data table (+)
Polar graphs
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