GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Reynolds number: 50,000 Max Cl/Cd: 38.12 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe301-il-50000-n5.txt Download as CSV file: xf-goe301-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 301 (FRIEDRICHSHAFEN G 13) 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 -0.2619 0.11272 0.10647 -0.0278 1.0000 0.0820
-7.750 -0.2785 0.11262 0.10653 -0.0254 1.0000 0.0829
-7.500 -0.2970 0.11276 0.10683 -0.0233 1.0000 0.0835
-7.250 -0.2879 0.11184 0.10595 -0.0341 0.9906 0.0844
-7.000 -0.2710 0.10499 0.09912 -0.0285 0.9893 0.0870
-6.750 -0.2481 0.10085 0.09497 -0.0324 0.9809 0.0907
-6.500 -0.2240 0.09722 0.09131 -0.0397 0.9693 0.0951
-6.250 -0.1872 0.09516 0.08912 -0.0587 0.9528 0.0985
-6.000 -0.1772 0.08934 0.08338 -0.0526 0.9474 0.1012
-5.750 -0.1533 0.08565 0.07965 -0.0556 0.9387 0.1078
-5.250 -0.1024 0.07838 0.07227 -0.0674 0.9163 0.1182
-5.000 -0.0721 0.07479 0.06860 -0.0723 0.9079 0.1257
-4.750 -0.0421 0.07135 0.06504 -0.0794 0.8958 0.1334
-4.500 -0.0034 0.06811 0.06162 -0.0871 0.8873 0.1485
-4.250 0.0145 0.06472 0.05828 -0.0860 0.8775 0.1561
-4.000 0.0466 0.06149 0.05494 -0.0908 0.8679 0.1691
-3.750 0.0806 0.05833 0.05166 -0.0952 0.8593 0.1850
-3.500 0.1069 0.05573 0.04897 -0.0974 0.8484 0.2022
-3.250 0.1390 0.05287 0.04604 -0.1003 0.8413 0.2340
-2.750 0.2642 0.04391 0.03557 -0.1189 0.8248 0.0959
-2.500 0.2937 0.04175 0.03318 -0.1203 0.8137 0.0931
-2.250 0.3331 0.03951 0.03057 -0.1231 0.8060 0.0935
-2.000 0.3676 0.03761 0.02835 -0.1249 0.7964 0.0926
-1.750 0.4030 0.03581 0.02616 -0.1265 0.7873 0.0906
-1.500 0.4408 0.03409 0.02403 -0.1282 0.7792 0.0894
-1.250 0.4725 0.03290 0.02253 -0.1289 0.7691 0.0904
-1.000 0.5104 0.03161 0.02086 -0.1303 0.7617 0.0938
-0.750 0.5393 0.03080 0.01976 -0.1303 0.7508 0.0953
-0.500 0.5739 0.02981 0.01843 -0.1310 0.7425 0.0963
-0.250 0.6043 0.02914 0.01745 -0.1309 0.7323 0.0980
0.000 0.6331 0.02848 0.01670 -0.1309 0.7224 0.1027
0.250 0.6662 0.02789 0.01588 -0.1312 0.7138 0.1084
0.500 0.6930 0.02763 0.01541 -0.1306 0.7027 0.1120
0.750 0.7250 0.02710 0.01477 -0.1308 0.6943 0.1195
1.000 0.7504 0.02702 0.01461 -0.1302 0.6833 0.1287
1.250 0.7779 0.02684 0.01439 -0.1299 0.6733 0.1381
1.500 0.8073 0.02665 0.01417 -0.1299 0.6639 0.1561
1.750 0.8323 0.02671 0.01428 -0.1294 0.6531 0.1793
2.000 0.8590 0.02485 0.01409 -0.1288 0.6453 1.0000
2.250 0.8813 0.02540 0.01434 -0.1276 0.6337 1.0000
2.500 0.9080 0.02576 0.01444 -0.1271 0.6243 1.0000
2.750 0.9337 0.02614 0.01463 -0.1265 0.6144 1.0000
3.000 0.9566 0.02665 0.01502 -0.1257 0.6039 1.0000
3.250 0.9855 0.02687 0.01506 -0.1255 0.5955 1.0000
3.500 1.0056 0.02749 0.01566 -0.1243 0.5842 1.0000
3.750 1.0308 0.02787 0.01595 -0.1237 0.5751 1.0000
4.000 1.0546 0.02829 0.01631 -0.1229 0.5653 1.0000
4.250 1.0759 0.02887 0.01688 -0.1219 0.5552 1.0000
4.500 1.1034 0.02910 0.01701 -0.1215 0.5471 1.0000
4.750 1.1216 0.02983 0.01779 -0.1202 0.5365 1.0000
5.000 1.1470 0.03018 0.01810 -0.1196 0.5282 1.0000
5.250 1.1672 0.03081 0.01878 -0.1185 0.5187 1.0000
5.500 1.1890 0.03138 0.01935 -0.1176 0.5100 1.0000
5.750 1.2121 0.03184 0.01985 -0.1167 0.5014 1.0000
6.000 1.2310 0.03259 0.02066 -0.1155 0.4924 1.0000
6.250 1.2562 0.03295 0.02102 -0.1149 0.4846 1.0000
6.500 1.2724 0.03386 0.02203 -0.1134 0.4753 1.0000
6.750 1.2993 0.03414 0.02231 -0.1130 0.4679 1.0000
7.000 1.3125 0.03523 0.02354 -0.1111 0.4583 1.0000
7.250 1.3411 0.03542 0.02371 -0.1109 0.4512 1.0000
7.500 1.3509 0.03668 0.02516 -0.1087 0.4410 1.0000
7.750 1.3741 0.03710 0.02560 -0.1078 0.4325 1.0000
8.000 1.3886 0.03791 0.02651 -0.1060 0.4220 1.0000
8.250 1.4008 0.03880 0.02750 -0.1039 0.4113 1.0000
8.500 1.4246 0.03897 0.02766 -0.1029 0.4015 1.0000
8.750 1.4294 0.04024 0.02911 -0.1000 0.3906 1.0000
9.000 1.4402 0.04122 0.03019 -0.0979 0.3810 1.0000
9.250 1.4552 0.04199 0.03103 -0.0962 0.3723 1.0000
9.500 1.4560 0.04359 0.03281 -0.0930 0.3639 1.0000
9.750 1.4720 0.04436 0.03369 -0.0915 0.3561 1.0000
10.000 1.4679 0.04642 0.03594 -0.0883 0.3480 1.0000
10.250 1.4832 0.04722 0.03683 -0.0868 0.3404 1.0000
10.500 1.4734 0.04985 0.03966 -0.0837 0.3324 1.0000
10.750 1.4887 0.05064 0.04052 -0.0823 0.3249 1.0000
11.000 1.4717 0.05414 0.04424 -0.0794 0.3169 1.0000
11.250 1.4872 0.05491 0.04511 -0.0781 0.3097 1.0000
11.500 1.4623 0.05962 0.05004 -0.0760 0.3019 1.0000
11.750 1.4757 0.06065 0.05116 -0.0747 0.2950 1.0000
12.000 1.4443 0.06680 0.05750 -0.0736 0.2874 1.0000
12.250 1.4479 0.06911 0.05994 -0.0727 0.2809 1.0000
12.500 1.4116 0.07684 0.06783 -0.0730 0.2731 1.0000
12.750 1.3976 0.08191 0.07301 -0.0731 0.2661 1.0000
13.000 1.4461 0.07815 0.06936 -0.0707 0.2629 1.0000
13.250 1.3326 0.09900 0.09029 -0.0765 0.2500 1.0000
13.500 1.3690 0.09624 0.08768 -0.0740 0.2478 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)