GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Reynolds number: 50,000 Max Cl/Cd: 37.11 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe331-il-50000-n5.txt Download as CSV file: xf-goe331-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 331 (PFALZ 60) 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 -0.2002 0.11204 0.10571 -0.0456 0.9661 0.0781
-7.750 -0.1891 0.10958 0.10324 -0.0495 0.9591 0.0807
-7.500 -0.1859 0.10836 0.10205 -0.0542 0.9475 0.0825
-7.000 -0.1599 0.10129 0.09500 -0.0585 0.9333 0.0853
-6.750 -0.1398 0.09763 0.09131 -0.0611 0.9286 0.0887
-6.500 -0.1332 0.09556 0.08926 -0.0629 0.9187 0.0921
-6.250 -0.1149 0.09552 0.08907 -0.0754 0.9069 0.0959
-6.000 -0.1054 0.09013 0.08378 -0.0708 0.9028 0.0981
-5.750 -0.0853 0.08662 0.08027 -0.0723 0.8982 0.1026
-5.500 -0.0737 0.08470 0.07830 -0.0751 0.8889 0.1076
-5.250 -0.0446 0.08190 0.07537 -0.0834 0.8827 0.1118
-5.000 -0.0380 0.07885 0.07238 -0.0809 0.8755 0.1146
-4.750 -0.0174 0.07611 0.06960 -0.0831 0.8694 0.1208
-4.500 0.0118 0.07377 0.06708 -0.0899 0.8627 0.1281
-4.250 0.0218 0.07097 0.06434 -0.0881 0.8557 0.1328
-4.000 0.0564 0.06813 0.06134 -0.0941 0.8512 0.1455
-3.750 0.0668 0.06626 0.05948 -0.0931 0.8429 0.1542
-3.500 0.0927 0.06357 0.05671 -0.0957 0.8375 0.1666
-3.250 0.1272 0.06076 0.05379 -0.0997 0.8339 0.1849
-3.000 0.1367 0.05930 0.05231 -0.0989 0.8243 0.1990
-2.750 0.1657 0.05684 0.04979 -0.1014 0.8197 0.2306
-2.250 0.2008 0.05359 0.04651 -0.1011 0.8059 0.3140
-1.250 0.4090 0.04548 0.03636 -0.1208 0.7827 0.1256
-1.000 0.4331 0.04390 0.03460 -0.1201 0.7707 0.1068
-0.750 0.4838 0.04151 0.03174 -0.1227 0.7650 0.0920
-0.500 0.5073 0.04047 0.03048 -0.1218 0.7525 0.0874
-0.250 0.5548 0.03907 0.02849 -0.1235 0.7470 0.0832
0.000 0.5727 0.03846 0.02780 -0.1220 0.7350 0.0825
0.500 0.6312 0.03654 0.02556 -0.1218 0.7181 0.0792
0.750 0.6709 0.03522 0.02397 -0.1227 0.7125 0.0773
1.000 0.6892 0.03504 0.02366 -0.1209 0.7003 0.0763
1.250 0.7269 0.03395 0.02231 -0.1214 0.6941 0.0758
1.500 0.7474 0.03377 0.02202 -0.1198 0.6819 0.0769
1.750 0.7717 0.03340 0.02153 -0.1187 0.6709 0.0785
2.250 0.8253 0.03240 0.02031 -0.1169 0.6498 0.0803
2.500 0.8496 0.03208 0.01991 -0.1158 0.6381 0.0811
2.750 0.8830 0.03131 0.01899 -0.1157 0.6288 0.0827
3.000 0.9036 0.03123 0.01889 -0.1143 0.6146 0.0859
3.250 0.9261 0.03113 0.01874 -0.1131 0.6006 0.0909
3.750 0.9769 0.03077 0.01825 -0.1114 0.5732 0.1034
4.000 1.0049 0.03050 0.01796 -0.1109 0.5597 0.1216
4.250 1.0261 0.02901 0.01781 -0.1092 0.5464 1.0000
4.500 1.0481 0.02933 0.01788 -0.1079 0.5313 1.0000
4.750 1.0701 0.02970 0.01803 -0.1067 0.5167 1.0000
5.000 1.0924 0.03009 0.01823 -0.1057 0.5028 1.0000
5.250 1.1158 0.03047 0.01843 -0.1048 0.4901 1.0000
5.500 1.1415 0.03076 0.01853 -0.1042 0.4787 1.0000
5.750 1.1595 0.03152 0.01921 -0.1029 0.4665 1.0000
6.000 1.1812 0.03213 0.01974 -0.1021 0.4564 1.0000
6.250 1.2049 0.03266 0.02015 -0.1015 0.4473 1.0000
6.500 1.2231 0.03349 0.02097 -0.1003 0.4380 1.0000
6.750 1.2484 0.03399 0.02139 -0.1000 0.4303 1.0000
7.000 1.2648 0.03495 0.02237 -0.0987 0.4223 1.0000
7.250 1.2885 0.03560 0.02300 -0.0982 0.4156 1.0000
7.500 1.3100 0.03643 0.02383 -0.0976 0.4095 1.0000
7.750 1.3261 0.03746 0.02495 -0.0964 0.4030 1.0000
8.000 1.3544 0.03800 0.02545 -0.0965 0.3976 1.0000
8.250 1.3669 0.03925 0.02681 -0.0949 0.3917 1.0000
8.500 1.3828 0.04037 0.02804 -0.0937 0.3861 1.0000
8.750 1.4106 0.04103 0.02871 -0.0939 0.3817 1.0000
9.000 1.4240 0.04237 0.03018 -0.0926 0.3770 1.0000
9.250 1.4306 0.04402 0.03200 -0.0905 0.3718 1.0000
9.500 1.4510 0.04501 0.03309 -0.0899 0.3671 1.0000
9.750 1.4814 0.04564 0.03374 -0.0904 0.3630 1.0000
10.000 1.4687 0.04835 0.03673 -0.0865 0.3583 1.0000
10.250 1.4710 0.05042 0.03898 -0.0844 0.3537 1.0000
10.500 1.4952 0.05122 0.03988 -0.0842 0.3493 1.0000
10.750 1.5049 0.05289 0.04168 -0.0828 0.3449 1.0000
11.000 1.4667 0.05782 0.04690 -0.0783 0.3397 1.0000
11.250 1.4677 0.06020 0.04942 -0.0767 0.3346 1.0000
11.500 1.5311 0.05789 0.04709 -0.0784 0.3300 1.0000
11.750 1.3315 0.08086 0.07047 -0.0732 0.3196 1.0000
12.000 1.3618 0.07996 0.06969 -0.0721 0.3160 1.0000
12.250 1.4317 0.07451 0.06430 -0.0709 0.3138 1.0000
12.500 1.2596 0.10199 0.09190 -0.0755 0.2975 1.0000
12.750 1.2933 0.09996 0.08999 -0.0736 0.2956 1.0000
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Polar data table (+)
Polar graphs
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