GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 456 AIRFOIL (goe456-il) Reynolds number: 100,000 Max Cl/Cd: 65.14 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe456-il-100000.txt Download as CSV file: xf-goe456-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 456 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3382 0.09802 0.09376 -0.0268 1.0000 0.0684
-7.000 -0.3565 0.09772 0.09358 -0.0242 1.0000 0.0690
-6.750 -0.3699 0.09711 0.09308 -0.0246 1.0000 0.0697
-6.500 -0.3779 0.09622 0.09225 -0.0277 1.0000 0.0701
-6.250 -0.3801 0.09300 0.08911 -0.0279 1.0000 0.0708
-6.000 -0.3784 0.08906 0.08520 -0.0202 1.0000 0.0730
-5.750 -0.3790 0.08681 0.08299 -0.0185 1.0000 0.0754
-5.500 -0.3791 0.08464 0.08086 -0.0187 1.0000 0.0783
-5.250 -0.3644 0.08275 0.07890 -0.0315 1.0000 0.0830
-5.000 -0.3649 0.07885 0.07508 -0.0289 1.0000 0.0842
-4.750 -0.3560 0.07573 0.07200 -0.0259 0.9977 0.0876
-4.500 -0.3049 0.07014 0.06621 -0.0410 0.9899 0.0977
-4.250 -0.2572 0.06552 0.06141 -0.0517 0.9832 0.1104
-4.000 -0.2230 0.06160 0.05739 -0.0572 0.9754 0.1241
-3.750 -0.1810 0.05731 0.05297 -0.0639 0.9698 0.1380
-3.500 -0.1571 0.05399 0.04967 -0.0645 0.9615 0.1453
-3.250 -0.1088 0.04972 0.04519 -0.0722 0.9563 0.1591
-3.000 -0.0329 0.03901 0.03317 -0.0871 0.9508 0.0965
-2.750 0.0129 0.03149 0.02489 -0.0913 0.9474 0.0668
-2.500 0.0606 0.02715 0.01947 -0.0948 0.9440 0.0601
-2.250 0.0960 0.02564 0.01759 -0.0963 0.9360 0.0660
-2.000 0.1395 0.02378 0.01522 -0.0986 0.9309 0.0685
-1.750 0.1741 0.02247 0.01379 -0.0995 0.9230 0.0745
-1.500 0.2161 0.02162 0.01298 -0.1020 0.9170 0.0998
-1.250 0.2493 0.02113 0.01282 -0.1029 0.9079 0.2325
-1.000 0.2916 0.02121 0.01290 -0.1059 0.9022 0.3082
-0.750 0.3200 0.02111 0.01278 -0.1062 0.8920 0.3451
-0.500 0.3607 0.02061 0.01229 -0.1085 0.8864 0.3730
-0.250 0.3951 0.02017 0.01199 -0.1098 0.8782 0.4221
0.000 0.4520 0.01843 0.01137 -0.1150 0.8760 1.0000
0.250 0.4809 0.01864 0.01133 -0.1152 0.8661 1.0000
0.500 0.5243 0.01852 0.01099 -0.1179 0.8616 1.0000
0.750 0.5496 0.01879 0.01114 -0.1175 0.8513 1.0000
1.000 0.5843 0.01884 0.01106 -0.1186 0.8447 1.0000
1.250 0.6147 0.01896 0.01111 -0.1190 0.8366 1.0000
1.500 0.6419 0.01921 0.01130 -0.1189 0.8279 1.0000
1.750 0.6771 0.01916 0.01122 -0.1200 0.8219 1.0000
2.000 0.7012 0.01948 0.01153 -0.1194 0.8123 1.0000
2.250 0.7413 0.01907 0.01109 -0.1207 0.8066 1.0000
2.500 0.7677 0.01903 0.01106 -0.1199 0.7949 1.0000
2.750 0.7973 0.01874 0.01082 -0.1193 0.7826 1.0000
3.000 0.8270 0.01839 0.01049 -0.1186 0.7701 1.0000
3.250 0.8555 0.01821 0.01033 -0.1180 0.7584 1.0000
3.500 0.8850 0.01810 0.01028 -0.1177 0.7488 1.0000
3.750 0.9141 0.01803 0.01034 -0.1173 0.7391 1.0000
4.000 0.9386 0.01817 0.01059 -0.1164 0.7276 1.0000
4.250 0.9643 0.01826 0.01079 -0.1156 0.7161 1.0000
4.500 0.9926 0.01793 0.01054 -0.1145 0.7005 1.0000
4.750 1.0208 0.01697 0.00952 -0.1123 0.6701 1.0000
5.000 1.0410 0.01661 0.00922 -0.1095 0.6345 1.0000
5.250 1.0597 0.01639 0.00889 -0.1063 0.5891 1.0000
5.500 1.0742 0.01649 0.00887 -0.1028 0.5318 1.0000
5.750 1.0842 0.01695 0.00902 -0.0988 0.4379 1.0000
6.000 1.0814 0.01884 0.00971 -0.0935 0.2707 1.0000
6.250 1.0827 0.02106 0.01099 -0.0895 0.1365 1.0000
6.500 1.0841 0.02338 0.01260 -0.0856 0.0546 1.0000
6.750 1.0983 0.02458 0.01399 -0.0831 0.0491 1.0000
7.000 1.1115 0.02582 0.01543 -0.0805 0.0460 1.0000
7.250 1.1221 0.02719 0.01698 -0.0777 0.0443 1.0000
7.500 1.1273 0.02878 0.01870 -0.0742 0.0427 1.0000
7.750 1.1290 0.03083 0.02079 -0.0704 0.0409 1.0000
8.000 1.1419 0.03230 0.02237 -0.0681 0.0393 1.0000
8.250 1.1638 0.03433 0.02442 -0.0669 0.0389 1.0000
8.500 1.2127 0.03755 0.02762 -0.0693 0.0397 1.0000
8.750 1.2669 0.04189 0.03209 -0.0723 0.0415 1.0000
9.000 1.2886 0.04309 0.03386 -0.0698 0.0449 1.0000
9.250 1.3182 0.04778 0.03906 -0.0690 0.0503 1.0000
9.500 1.3401 0.05071 0.04251 -0.0668 0.0551 1.0000
9.750 1.3470 0.05533 0.04783 -0.0634 0.0608 1.0000
10.000 1.3496 0.05943 0.05271 -0.0593 0.0697 1.0000
10.250 1.3434 0.06554 0.05957 -0.0551 0.0830 1.0000
10.500 1.3309 0.07684 0.07163 -0.0524 0.1114 1.0000
10.750 1.2932 0.07885 0.07397 -0.0472 0.1100 1.0000
11.000 1.2001 0.07199 0.06725 -0.0369 0.0906 1.0000
11.250 1.1680 0.07671 0.07218 -0.0350 0.0907 1.0000
11.500 1.1383 0.08197 0.07760 -0.0343 0.0904 1.0000
11.750 1.1068 0.08774 0.08353 -0.0348 0.0902 1.0000
12.000 1.0781 0.09391 0.08982 -0.0362 0.0897 1.0000
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Polar data table (+)
Polar graphs
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