GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Reynolds number: 50,000 Max Cl/Cd: 39.54 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe303-il-50000-n5.txt Download as CSV file: xf-goe303-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) 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 -0.3119 0.10687 0.10064 -0.0238 1.0000 0.1026
-7.250 -0.3235 0.10567 0.09955 -0.0217 1.0000 0.1041
-7.000 -0.3334 0.10434 0.09833 -0.0206 1.0000 0.1060
-6.750 -0.3343 0.10292 0.09697 -0.0258 0.9961 0.1091
-6.500 -0.3101 0.09832 0.09235 -0.0348 0.9870 0.1113
-6.250 -0.2911 0.09373 0.08777 -0.0327 0.9824 0.1159
-6.000 -0.2649 0.09004 0.08399 -0.0400 0.9734 0.1232
-5.750 -0.2321 0.08597 0.07980 -0.0530 0.9627 0.1273
-5.500 -0.2160 0.08183 0.07569 -0.0518 0.9547 0.1300
-5.250 -0.1899 0.07819 0.07199 -0.0555 0.9470 0.1358
-5.000 -0.1583 0.07435 0.06803 -0.0640 0.9373 0.1454
-4.750 -0.1208 0.07191 0.06529 -0.0736 0.9263 0.1593
-4.500 -0.0637 0.06268 0.05544 -0.0857 0.9205 0.0944
-4.250 -0.0482 0.05954 0.05245 -0.0844 0.9113 0.0909
-4.000 -0.0089 0.05558 0.04826 -0.0899 0.9051 0.0887
-3.750 0.0233 0.05228 0.04472 -0.0937 0.8955 0.0875
-3.500 0.0685 0.04804 0.04002 -0.0998 0.8895 0.0831
-3.250 0.1109 0.04426 0.03543 -0.1045 0.8809 0.0792
-3.000 0.1494 0.04152 0.03235 -0.1077 0.8744 0.0796
-2.750 0.1790 0.03983 0.03063 -0.1091 0.8658 0.0821
-2.500 0.2156 0.03792 0.02840 -0.1113 0.8586 0.0840
-2.250 0.2493 0.03611 0.02620 -0.1128 0.8503 0.0843
-2.000 0.2854 0.03442 0.02412 -0.1145 0.8428 0.0850
-1.750 0.3174 0.03311 0.02248 -0.1152 0.8341 0.0864
-1.500 0.3529 0.03193 0.02095 -0.1164 0.8268 0.0905
-1.250 0.3833 0.03109 0.01970 -0.1166 0.8175 0.0944
-1.000 0.4176 0.03003 0.01855 -0.1176 0.8106 0.0980
-0.750 0.4457 0.02947 0.01782 -0.1174 0.8009 0.1022
-0.250 0.5093 0.02834 0.01639 -0.1180 0.7844 0.1213
0.000 0.5452 0.02761 0.01559 -0.1189 0.7783 0.1384
0.250 0.5707 0.02738 0.01540 -0.1184 0.7679 0.1650
0.500 0.6066 0.02653 0.01475 -0.1195 0.7621 0.2274
0.750 0.6285 0.02457 0.01473 -0.1185 0.7517 1.0000
1.000 0.6617 0.02459 0.01427 -0.1187 0.7447 1.0000
1.500 0.7150 0.02513 0.01434 -0.1178 0.7256 1.0000
1.750 0.7443 0.02527 0.01429 -0.1177 0.7169 1.0000
2.000 0.7693 0.02561 0.01450 -0.1170 0.7065 1.0000
2.250 0.8029 0.02547 0.01418 -0.1173 0.6983 1.0000
2.500 0.8265 0.02571 0.01431 -0.1162 0.6849 1.0000
2.750 0.8516 0.02585 0.01435 -0.1152 0.6716 1.0000
3.000 0.8779 0.02594 0.01434 -0.1144 0.6587 1.0000
3.250 0.9064 0.02595 0.01423 -0.1139 0.6470 1.0000
3.500 0.9320 0.02614 0.01436 -0.1131 0.6351 1.0000
3.750 0.9544 0.02653 0.01475 -0.1121 0.6228 1.0000
4.000 0.9793 0.02682 0.01501 -0.1113 0.6116 1.0000
4.250 1.0080 0.02692 0.01504 -0.1110 0.6013 1.0000
4.500 1.0287 0.02739 0.01556 -0.1097 0.5885 1.0000
4.750 1.0509 0.02781 0.01599 -0.1087 0.5761 1.0000
5.000 1.0750 0.02812 0.01630 -0.1078 0.5642 1.0000
5.250 1.1014 0.02830 0.01648 -0.1072 0.5526 1.0000
5.500 1.1220 0.02877 0.01700 -0.1059 0.5391 1.0000
5.750 1.1424 0.02928 0.01756 -0.1046 0.5256 1.0000
6.000 1.1633 0.02976 0.01809 -0.1033 0.5123 1.0000
6.250 1.1847 0.03021 0.01860 -0.1022 0.4990 1.0000
6.500 1.2064 0.03065 0.01906 -0.1010 0.4856 1.0000
6.750 1.2285 0.03107 0.01950 -0.0999 0.4724 1.0000
7.000 1.2476 0.03168 0.02020 -0.0985 0.4587 1.0000
7.250 1.2652 0.03242 0.02103 -0.0969 0.4454 1.0000
7.500 1.2834 0.03315 0.02184 -0.0955 0.4326 1.0000
7.750 1.3028 0.03384 0.02257 -0.0942 0.4208 1.0000
8.000 1.3253 0.03437 0.02313 -0.0933 0.4101 1.0000
8.250 1.3397 0.03540 0.02431 -0.0915 0.3986 1.0000
8.500 1.3571 0.03631 0.02533 -0.0902 0.3886 1.0000
8.750 1.3798 0.03694 0.02598 -0.0893 0.3796 1.0000
9.000 1.3911 0.03820 0.02745 -0.0874 0.3698 1.0000
9.250 1.4108 0.03902 0.02834 -0.0863 0.3613 1.0000
9.500 1.4234 0.04009 0.02954 -0.0844 0.3517 1.0000
9.750 1.4315 0.04121 0.03079 -0.0819 0.3414 1.0000
10.000 1.4435 0.04199 0.03162 -0.0797 0.3308 1.0000
10.250 1.4499 0.04307 0.03279 -0.0770 0.3201 1.0000
10.500 1.4512 0.04461 0.03449 -0.0742 0.3102 1.0000
10.750 1.4630 0.04559 0.03551 -0.0723 0.3008 1.0000
11.000 1.4639 0.04736 0.03748 -0.0698 0.2921 1.0000
11.250 1.4703 0.04884 0.03907 -0.0678 0.2835 1.0000
11.500 1.4750 0.05045 0.04086 -0.0658 0.2748 1.0000
11.750 1.4743 0.05257 0.04315 -0.0637 0.2665 1.0000
12.000 1.4828 0.05389 0.04455 -0.0620 0.2574 1.0000
12.250 1.4726 0.05700 0.04791 -0.0600 0.2495 1.0000
12.500 1.4850 0.05801 0.04892 -0.0585 0.2402 1.0000
12.750 1.4653 0.06231 0.05354 -0.0569 0.2326 1.0000
13.000 1.4726 0.06381 0.05508 -0.0556 0.2234 1.0000
13.250 1.4512 0.06877 0.06032 -0.0548 0.2158 1.0000
13.500 1.4546 0.07084 0.06248 -0.0537 0.2071 1.0000
13.750 1.4303 0.07671 0.06862 -0.0538 0.1999 1.0000
14.000 1.4296 0.07942 0.07140 -0.0532 0.1917 1.0000
14.250 1.3984 0.08696 0.07919 -0.0546 0.1851 1.0000
14.500 1.3986 0.08969 0.08199 -0.0543 0.1774 1.0000
14.750 1.3489 0.10142 0.09395 -0.0583 0.1721 1.0000
15.000 1.3675 0.10099 0.09355 -0.0568 0.1644 1.0000
15.250 1.2650 0.12512 0.11777 -0.0683 0.1594 1.0000
15.500 1.2789 0.12556 0.11833 -0.0674 0.1535 1.0000
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Polar data table (+)
Polar graphs
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