GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 535 AIRFOIL (goe535-il) Reynolds number: 50,000 Max Cl/Cd: 29.44 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe535-il-50000-n5.txt Download as CSV file: xf-goe535-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 535 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2392 0.11896 0.11183 -0.0372 1.0000 0.1065
-9.500 -0.2355 0.11707 0.11000 -0.0350 1.0000 0.1045
-9.250 -0.2422 0.11538 0.10842 -0.0332 1.0000 0.1037
-9.000 -0.2442 0.11304 0.10616 -0.0333 0.9981 0.1029
-8.750 -0.2257 0.10838 0.10148 -0.0390 0.9891 0.1024
-8.500 -0.2083 0.10362 0.09670 -0.0448 0.9800 0.1011
-8.250 -0.1964 0.09865 0.09173 -0.0504 0.9687 0.0993
-8.000 -0.1881 0.09364 0.08670 -0.0559 0.9563 0.0984
-7.750 -0.1755 0.08949 0.08254 -0.0604 0.9439 0.0991
-7.500 -0.1631 0.08515 0.07820 -0.0653 0.9323 0.1001
-7.250 -0.1584 0.08072 0.07376 -0.0696 0.9178 0.1010
-7.000 -0.1567 0.07526 0.06829 -0.0750 0.9021 0.1012
-6.750 -0.1589 0.06768 0.06061 -0.0835 0.8866 0.1014
-6.500 -0.1657 0.05582 0.04830 -0.0997 0.8711 0.1029
-6.250 -0.1482 0.04674 0.03824 -0.1125 0.8600 0.1060
-6.000 -0.1252 0.04498 0.03645 -0.1131 0.8473 0.1081
-5.750 -0.0895 0.04266 0.03394 -0.1162 0.8395 0.1118
-5.500 -0.0664 0.04005 0.03087 -0.1181 0.8265 0.1155
-5.250 -0.0296 0.03777 0.02827 -0.1209 0.8187 0.1194
-5.000 -0.0056 0.03668 0.02711 -0.1207 0.8057 0.1231
-4.750 0.0322 0.03481 0.02482 -0.1230 0.7979 0.1282
-4.500 0.0563 0.03380 0.02370 -0.1227 0.7849 0.1321
-4.250 0.0934 0.03259 0.02237 -0.1240 0.7769 0.1373
-4.000 0.1181 0.03175 0.02127 -0.1236 0.7636 0.1423
-3.750 0.1541 0.03073 0.02023 -0.1245 0.7555 0.1479
-3.500 0.1774 0.03021 0.01962 -0.1237 0.7422 0.1532
-3.250 0.2136 0.02930 0.01855 -0.1246 0.7340 0.1604
-3.000 0.2358 0.02895 0.01820 -0.1235 0.7206 0.1665
-2.750 0.2718 0.02820 0.01729 -0.1244 0.7124 0.1758
-2.500 0.2931 0.02796 0.01709 -0.1233 0.6992 0.1848
-2.250 0.3275 0.02730 0.01638 -0.1239 0.6909 0.1984
-2.000 0.3498 0.02711 0.01626 -0.1231 0.6780 0.2149
-1.750 0.3842 0.02653 0.01580 -0.1239 0.6698 0.2488
-1.500 0.4048 0.02665 0.01636 -0.1225 0.6577 0.2972
-1.250 0.4350 0.02683 0.01656 -0.1220 0.6492 0.3672
-1.000 0.4567 0.02733 0.01700 -0.1206 0.6381 0.4088
-0.750 0.4834 0.02767 0.01728 -0.1195 0.6294 0.4392
-0.500 0.5067 0.02811 0.01765 -0.1182 0.6201 0.4638
-0.250 0.5294 0.02855 0.01807 -0.1167 0.6109 0.4909
0.000 0.5565 0.02887 0.01832 -0.1154 0.6040 0.5242
0.250 0.5719 0.02942 0.01895 -0.1130 0.5938 0.5482
0.500 0.5991 0.02951 0.01894 -0.1122 0.5866 0.5696
0.750 0.6229 0.02976 0.01910 -0.1114 0.5786 0.5842
1.000 0.6469 0.03003 0.01926 -0.1108 0.5701 0.5977
1.250 0.6782 0.02994 0.01904 -0.1109 0.5640 0.6087
1.500 0.6986 0.03044 0.01949 -0.1100 0.5554 0.6180
1.750 0.7245 0.03063 0.01961 -0.1096 0.5481 0.6266
2.000 0.7590 0.03061 0.01939 -0.1104 0.5426 0.6362
2.250 0.7747 0.03127 0.02012 -0.1090 0.5339 0.6434
2.500 0.8021 0.03155 0.02031 -0.1089 0.5272 0.6529
2.750 0.8363 0.03149 0.02013 -0.1096 0.5221 0.6624
3.000 0.8497 0.03238 0.02112 -0.1080 0.5135 0.6710
3.250 0.8760 0.03268 0.02139 -0.1077 0.5070 0.6806
3.500 0.9104 0.03266 0.02127 -0.1084 0.5021 0.6934
3.750 0.9208 0.03367 0.02246 -0.1064 0.4938 0.7042
4.000 0.9453 0.03404 0.02286 -0.1060 0.4872 0.7189
4.250 0.9791 0.03396 0.02276 -0.1065 0.4824 0.7380
4.500 0.9879 0.03504 0.02409 -0.1044 0.4745 0.7613
4.750 1.0100 0.03535 0.02462 -0.1037 0.4677 0.8306
5.000 1.0415 0.03538 0.02448 -0.1039 0.4627 1.0000
5.250 1.0486 0.03689 0.02604 -0.1019 0.4550 1.0000
5.500 1.0661 0.03783 0.02694 -0.1008 0.4480 1.0000
5.750 1.1018 0.03789 0.02681 -0.1016 0.4429 1.0000
6.000 1.1040 0.03958 0.02857 -0.0990 0.4355 1.0000
6.250 1.1132 0.04087 0.02987 -0.0971 0.4284 1.0000
6.500 1.1486 0.04086 0.02970 -0.0976 0.4233 1.0000
6.750 1.1462 0.04272 0.03163 -0.0945 0.4164 1.0000
7.000 1.1375 0.04485 0.03382 -0.0909 0.4088 1.0000
7.250 1.1729 0.04475 0.03362 -0.0913 0.4040 1.0000
7.500 1.1702 0.04676 0.03567 -0.0885 0.3977 1.0000
7.750 1.1331 0.05122 0.04030 -0.0842 0.3885 1.0000
8.000 1.1712 0.05062 0.03960 -0.0842 0.3845 1.0000
8.250 1.0841 0.06067 0.04991 -0.0807 0.3705 1.0000
8.500 1.1103 0.06074 0.04994 -0.0799 0.3665 1.0000
8.750 1.1540 0.05912 0.04825 -0.0793 0.3641 1.0000
9.250 1.0745 0.07414 0.06349 -0.0791 0.3423 1.0000
9.750 1.0613 0.08281 0.07226 -0.0797 0.3271 1.0000
10.750 1.0023 0.10676 0.09642 -0.0846 0.2947 1.0000
11.000 1.0252 0.10708 0.09674 -0.0837 0.2925 1.0000
11.500 0.9925 0.12027 0.11005 -0.0877 0.2786 1.0000
11.750 1.0117 0.12123 0.11102 -0.0871 0.2762 1.0000
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Polar data table (+)
Polar graphs
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