GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Reynolds number: 50,000 Max Cl/Cd: 38.09 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe300-il-50000-n5.txt Download as CSV file: xf-goe300-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) 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 -0.2633 0.11372 0.10765 -0.0277 1.0000 0.0723
-7.750 -0.2792 0.11368 0.10775 -0.0252 1.0000 0.0725
-7.500 -0.2920 0.11333 0.10753 -0.0239 1.0000 0.0726
-7.250 -0.2781 0.11132 0.10553 -0.0315 0.9917 0.0729
-7.000 -0.2589 0.10456 0.09880 -0.0310 0.9871 0.0739
-6.750 -0.2379 0.09959 0.09381 -0.0329 0.9800 0.0757
-6.500 -0.2150 0.09554 0.08973 -0.0375 0.9709 0.0779
-6.250 -0.1906 0.09193 0.08609 -0.0434 0.9607 0.0817
-6.000 -0.1557 0.08995 0.08399 -0.0568 0.9468 0.0858
-5.500 -0.1101 0.08057 0.07458 -0.0626 0.9306 0.0890
-5.250 -0.0867 0.07700 0.07097 -0.0658 0.9206 0.0921
-5.000 -0.0421 0.07483 0.06854 -0.0776 0.9098 0.1001
-4.750 -0.0193 0.07029 0.06399 -0.0800 0.9010 0.1023
-4.500 0.0011 0.06672 0.06039 -0.0809 0.8914 0.1060
-4.250 0.0514 0.06471 0.05798 -0.0912 0.8823 0.1156
-4.000 0.0631 0.06054 0.05392 -0.0899 0.8717 0.1192
-3.750 0.1109 0.05853 0.05148 -0.0975 0.8642 0.1309
-3.500 0.1249 0.05470 0.04775 -0.0966 0.8533 0.1346
-3.250 0.1546 0.05215 0.04504 -0.0993 0.8441 0.1494
-3.000 0.1985 0.04838 0.04080 -0.1038 0.8358 0.1116
-2.750 0.2306 0.04590 0.03803 -0.1060 0.8262 0.1114
-2.500 0.2672 0.04311 0.03490 -0.1086 0.8184 0.1070
-2.250 0.2980 0.04137 0.03284 -0.1100 0.8085 0.1116
-2.000 0.3344 0.03917 0.03027 -0.1119 0.8012 0.1109
-1.750 0.3668 0.03801 0.02856 -0.1129 0.7908 0.1155
-1.500 0.4019 0.03604 0.02631 -0.1142 0.7838 0.1169
-1.250 0.4295 0.03479 0.02476 -0.1142 0.7718 0.1172
-1.000 0.4576 0.03363 0.02346 -0.1142 0.7610 0.1225
-0.750 0.4913 0.03243 0.02191 -0.1147 0.7519 0.1261
-0.500 0.5187 0.03158 0.02078 -0.1143 0.7398 0.1263
-0.250 0.5486 0.03075 0.01965 -0.1142 0.7297 0.1270
0.000 0.5792 0.02998 0.01858 -0.1141 0.7206 0.1283
0.250 0.6053 0.02956 0.01798 -0.1136 0.7098 0.1330
0.500 0.6361 0.02888 0.01713 -0.1136 0.7023 0.1385
0.750 0.6619 0.02867 0.01673 -0.1130 0.6909 0.1405
1.000 0.6913 0.02829 0.01611 -0.1126 0.6820 0.1425
1.250 0.7192 0.02802 0.01565 -0.1121 0.6725 0.1449
1.500 0.7452 0.02783 0.01537 -0.1115 0.6626 0.1477
1.750 0.7736 0.02748 0.01495 -0.1111 0.6541 0.1522
2.000 0.7973 0.02758 0.01497 -0.1103 0.6435 0.1610
2.250 0.8261 0.02724 0.01462 -0.1099 0.6358 0.1713
2.500 0.8488 0.02740 0.01478 -0.1091 0.6247 0.1783
2.750 0.8749 0.02739 0.01474 -0.1086 0.6156 0.1877
3.000 0.9008 0.02741 0.01479 -0.1082 0.6062 0.2032
3.250 0.9252 0.02755 0.01507 -0.1077 0.5965 0.2326
3.500 0.9505 0.02629 0.01509 -0.1069 0.5885 1.0000
3.750 0.9730 0.02689 0.01551 -0.1060 0.5782 1.0000
4.000 1.0015 0.02709 0.01548 -0.1056 0.5706 1.0000
4.250 1.0219 0.02781 0.01618 -0.1046 0.5599 1.0000
4.500 1.0490 0.02813 0.01637 -0.1042 0.5524 1.0000
4.750 1.0696 0.02889 0.01715 -0.1033 0.5427 1.0000
5.000 1.0951 0.02930 0.01752 -0.1027 0.5347 1.0000
5.250 1.1164 0.02992 0.01815 -0.1018 0.5247 1.0000
5.500 1.1382 0.03048 0.01872 -0.1008 0.5149 1.0000
5.750 1.1631 0.03079 0.01901 -0.1001 0.5058 1.0000
6.000 1.1811 0.03158 0.01988 -0.0989 0.4952 1.0000
6.250 1.2066 0.03178 0.02006 -0.0981 0.4862 1.0000
6.500 1.2241 0.03249 0.02087 -0.0968 0.4752 1.0000
6.750 1.2428 0.03312 0.02158 -0.0955 0.4649 1.0000
7.000 1.2675 0.03328 0.02172 -0.0946 0.4557 1.0000
7.250 1.2809 0.03423 0.02284 -0.0929 0.4446 1.0000
7.500 1.3012 0.03477 0.02346 -0.0918 0.4358 1.0000
7.750 1.3188 0.03550 0.02430 -0.0905 0.4267 1.0000
8.000 1.3341 0.03636 0.02531 -0.0890 0.4173 1.0000
8.250 1.3566 0.03664 0.02564 -0.0879 0.4083 1.0000
8.500 1.3659 0.03782 0.02700 -0.0859 0.3976 1.0000
8.750 1.3829 0.03844 0.02771 -0.0844 0.3879 1.0000
9.000 1.3992 0.03910 0.02849 -0.0828 0.3779 1.0000
9.250 1.4072 0.04034 0.02989 -0.0806 0.3673 1.0000
9.500 1.4243 0.04091 0.03052 -0.0791 0.3571 1.0000
9.750 1.4322 0.04200 0.03172 -0.0767 0.3461 1.0000
10.000 1.4355 0.04350 0.03339 -0.0742 0.3352 1.0000
10.250 1.4502 0.04427 0.03420 -0.0726 0.3245 1.0000
10.500 1.4517 0.04604 0.03612 -0.0703 0.3138 1.0000
10.750 1.4530 0.04797 0.03820 -0.0682 0.3036 1.0000
11.000 1.4697 0.04870 0.03896 -0.0668 0.2940 1.0000
11.250 1.4551 0.05213 0.04263 -0.0645 0.2846 1.0000
11.500 1.4663 0.05340 0.04399 -0.0631 0.2762 1.0000
11.750 1.4529 0.05715 0.04797 -0.0616 0.2680 1.0000
12.000 1.4638 0.05853 0.04942 -0.0604 0.2610 1.0000
12.250 1.4424 0.06357 0.05471 -0.0596 0.2539 1.0000
12.500 1.4617 0.06398 0.05519 -0.0583 0.2478 1.0000
12.750 1.4229 0.07173 0.06319 -0.0588 0.2415 1.0000
13.000 1.4203 0.07505 0.06664 -0.0584 0.2359 1.0000
13.250 1.4125 0.07924 0.07097 -0.0584 0.2309 1.0000
13.500 1.3406 0.09393 0.08579 -0.0629 0.2236 1.0000
13.750 1.3722 0.09189 0.08390 -0.0606 0.2201 1.0000
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Polar data table (+)
Polar graphs
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