GOE 287 AIRFOIL (goe287-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 287 AIRFOIL (goe287-il) Reynolds number: 50,000 Max Cl/Cd: 38.04 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe287-il-50000-n5.txt Download as CSV file: xf-goe287-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 287 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 -0.3257 0.10318 0.09717 -0.0214 1.0000 0.0900
-7.750 -0.3284 0.10179 0.09591 -0.0265 1.0000 0.0920
-7.500 -0.3257 0.10011 0.09433 -0.0342 1.0000 0.0927
-7.250 -0.3102 0.09371 0.08798 -0.0268 1.0000 0.0976
-7.000 -0.3052 0.09106 0.08543 -0.0288 1.0000 0.1027
-6.750 -0.3110 0.09005 0.08455 -0.0329 1.0000 0.1062
-6.500 -0.2956 0.08565 0.08019 -0.0367 0.9876 0.1091
-6.250 -0.2697 0.08110 0.07559 -0.0401 0.9729 0.1156
-6.000 -0.2388 0.07667 0.07103 -0.0512 0.9542 0.1231
-5.750 -0.2145 0.07268 0.06696 -0.0537 0.9394 0.1324
-5.500 -0.1909 0.06885 0.06306 -0.0576 0.9235 0.1444
-5.250 -0.1679 0.06535 0.05946 -0.0613 0.9073 0.1581
-5.000 -0.1450 0.06201 0.05599 -0.0647 0.8919 0.1717
-4.750 -0.1226 0.05890 0.05276 -0.0670 0.8785 0.1878
-4.500 -0.1011 0.05615 0.04987 -0.0692 0.8655 0.2144
-4.000 -0.0092 0.04559 0.03792 -0.0828 0.8434 0.0887
-3.750 0.0204 0.04244 0.03436 -0.0845 0.8337 0.0829
-3.500 0.0551 0.03979 0.03090 -0.0863 0.8239 0.0773
-3.250 0.0840 0.03781 0.02842 -0.0871 0.8140 0.0778
-3.000 0.1089 0.03568 0.02622 -0.0875 0.8059 0.0806
-2.750 0.1377 0.03402 0.02413 -0.0880 0.7968 0.0805
-2.500 0.1678 0.03253 0.02209 -0.0883 0.7893 0.0790
-2.250 0.1968 0.03131 0.02045 -0.0884 0.7813 0.0784
-2.000 0.2252 0.03019 0.01900 -0.0885 0.7739 0.0783
-1.750 0.2533 0.02917 0.01769 -0.0885 0.7666 0.0786
-1.500 0.2814 0.02828 0.01657 -0.0885 0.7601 0.0793
-1.250 0.3086 0.02760 0.01575 -0.0885 0.7534 0.0813
-1.000 0.3361 0.02706 0.01504 -0.0882 0.7484 0.0862
-0.750 0.3639 0.02676 0.01454 -0.0883 0.7412 0.0905
-0.500 0.3922 0.02637 0.01392 -0.0880 0.7358 0.0925
-0.250 0.4194 0.02600 0.01349 -0.0879 0.7301 0.0954
0.000 0.4463 0.02582 0.01325 -0.0880 0.7244 0.0996
0.250 0.4738 0.02564 0.01294 -0.0878 0.7199 0.1055
0.500 0.5004 0.02561 0.01292 -0.0880 0.7139 0.1147
0.750 0.5275 0.02549 0.01288 -0.0881 0.7085 0.1380
1.000 0.5530 0.02327 0.01269 -0.0872 0.7041 1.0000
1.250 0.5782 0.02375 0.01288 -0.0870 0.6953 1.0000
1.500 0.6043 0.02387 0.01274 -0.0862 0.6870 1.0000
1.750 0.6295 0.02396 0.01262 -0.0852 0.6762 1.0000
2.000 0.6542 0.02407 0.01258 -0.0842 0.6640 1.0000
2.250 0.6791 0.02416 0.01253 -0.0832 0.6523 1.0000
2.500 0.7053 0.02419 0.01242 -0.0823 0.6435 1.0000
2.750 0.7303 0.02454 0.01272 -0.0819 0.6341 1.0000
3.000 0.7558 0.02483 0.01298 -0.0814 0.6260 1.0000
3.250 0.7816 0.02505 0.01316 -0.0808 0.6177 1.0000
3.500 0.8062 0.02544 0.01356 -0.0804 0.6082 1.0000
3.750 0.8330 0.02551 0.01360 -0.0797 0.6007 1.0000
4.000 0.8568 0.02596 0.01412 -0.0792 0.5897 1.0000
4.250 0.8815 0.02627 0.01448 -0.0786 0.5795 1.0000
4.500 0.9080 0.02632 0.01454 -0.0778 0.5706 1.0000
4.750 0.9315 0.02674 0.01507 -0.0773 0.5585 1.0000
5.000 0.9553 0.02711 0.01555 -0.0766 0.5463 1.0000
5.250 0.9794 0.02742 0.01596 -0.0759 0.5339 1.0000
5.500 1.0034 0.02769 0.01636 -0.0751 0.5208 1.0000
5.750 1.0270 0.02799 0.01676 -0.0743 0.5067 1.0000
6.000 1.0498 0.02836 0.01727 -0.0735 0.4916 1.0000
6.250 1.0720 0.02881 0.01787 -0.0726 0.4760 1.0000
6.500 1.0940 0.02933 0.01859 -0.0718 0.4608 1.0000
6.750 1.1158 0.02989 0.01931 -0.0710 0.4461 1.0000
7.000 1.1375 0.03046 0.02004 -0.0702 0.4322 1.0000
7.250 1.1595 0.03102 0.02074 -0.0694 0.4196 1.0000
7.500 1.1827 0.03146 0.02135 -0.0685 0.4088 1.0000
7.750 1.2031 0.03193 0.02195 -0.0674 0.3944 1.0000
8.000 1.2183 0.03203 0.02202 -0.0655 0.3679 1.0000
8.250 1.2315 0.03260 0.02250 -0.0635 0.3421 1.0000
8.500 1.2413 0.03356 0.02335 -0.0615 0.3162 1.0000
8.750 1.2506 0.03474 0.02455 -0.0596 0.2955 1.0000
9.000 1.2570 0.03620 0.02610 -0.0577 0.2756 1.0000
9.250 1.2562 0.03799 0.02791 -0.0554 0.2521 1.0000
9.500 1.2559 0.03996 0.02999 -0.0536 0.2316 1.0000
9.750 1.2538 0.04242 0.03255 -0.0523 0.2055 1.0000
10.250 1.2346 0.04967 0.03924 -0.0511 0.0974 1.0000
10.500 1.2181 0.05455 0.04370 -0.0508 0.0616 1.0000
10.750 1.2092 0.05880 0.04788 -0.0507 0.0548 1.0000
11.000 1.2014 0.06307 0.05220 -0.0508 0.0510 1.0000
11.250 1.1945 0.06734 0.05663 -0.0512 0.0482 1.0000
11.500 1.1862 0.07189 0.06134 -0.0517 0.0462 1.0000
11.750 1.1769 0.07668 0.06628 -0.0525 0.0447 1.0000
12.000 1.1670 0.08164 0.07139 -0.0535 0.0435 1.0000
12.250 1.1572 0.08665 0.07653 -0.0545 0.0427 1.0000
12.500 1.1486 0.09158 0.08156 -0.0556 0.0419 1.0000
12.750 1.1441 0.09595 0.08615 -0.0564 0.0412 1.0000
13.000 1.1410 0.10009 0.09045 -0.0572 0.0404 1.0000
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Polar data table (+)
Polar graphs
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