GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 495 AIRFOIL (goe495-il) Reynolds number: 100,000 Max Cl/Cd: 69.21 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe495-il-100000.txt Download as CSV file: xf-goe495-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 495 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3489 0.09993 0.09521 -0.0309 1.0000 0.0822
-7.500 -0.3696 0.10012 0.09555 -0.0290 1.0000 0.0828
-7.250 -0.3835 0.09967 0.09522 -0.0303 1.0000 0.0832
-7.000 -0.3913 0.09810 0.09376 -0.0332 1.0000 0.0836
-6.750 -0.3770 0.09187 0.08750 -0.0231 1.0000 0.0864
-6.500 -0.3787 0.08985 0.08553 -0.0209 1.0000 0.0885
-6.250 -0.3827 0.08797 0.08371 -0.0198 1.0000 0.0910
-6.000 -0.3865 0.08607 0.08186 -0.0208 1.0000 0.0944
-5.750 -0.3778 0.08341 0.07920 -0.0358 1.0000 0.0976
-5.500 -0.3817 0.08009 0.07596 -0.0275 1.0000 0.0990
-5.250 -0.3794 0.07770 0.07360 -0.0238 1.0000 0.1016
-5.000 -0.3434 0.07335 0.06907 -0.0431 1.0000 0.1116
-4.750 -0.3495 0.07045 0.06630 -0.0350 1.0000 0.1130
-4.500 -0.3469 0.06854 0.06441 -0.0306 1.0000 0.1174
-4.250 -0.3184 0.06401 0.05978 -0.0397 1.0000 0.1278
-4.000 -0.3090 0.06170 0.05748 -0.0379 1.0000 0.1323
-3.750 -0.2491 0.05692 0.05223 -0.0558 1.0000 0.1545
-3.500 -0.2431 0.05341 0.04889 -0.0525 1.0000 0.1565
-3.250 -0.2035 0.04992 0.04530 -0.0577 0.9956 0.1724
-3.000 -0.0944 0.03329 0.02698 -0.0821 0.9976 0.0942
-2.750 -0.0429 0.02889 0.02178 -0.0880 0.9949 0.0915
-2.500 0.0031 0.02619 0.01836 -0.0919 0.9909 0.0928
-2.250 0.0470 0.02454 0.01605 -0.0949 0.9864 0.0964
-2.000 0.0875 0.02348 0.01485 -0.0977 0.9816 0.1041
-1.750 0.1266 0.02264 0.01366 -0.0998 0.9754 0.1111
-1.500 0.1690 0.02202 0.01308 -0.1028 0.9709 0.1274
-1.250 0.2032 0.02144 0.01258 -0.1042 0.9633 0.1550
-1.000 0.2451 0.02072 0.01230 -0.1072 0.9581 0.2585
-0.750 0.2777 0.02064 0.01248 -0.1086 0.9498 0.3366
-0.500 0.3196 0.02051 0.01270 -0.1115 0.9440 0.4487
-0.250 0.3509 0.02002 0.01275 -0.1122 0.9359 0.5976
0.000 0.3921 0.01924 0.01247 -0.1144 0.9300 1.0000
0.500 0.4666 0.01974 0.01256 -0.1183 0.9135 1.0000
0.750 0.4998 0.01998 0.01267 -0.1195 0.9039 1.0000
1.000 0.5338 0.02021 0.01280 -0.1207 0.8946 1.0000
1.250 0.5773 0.02024 0.01278 -0.1235 0.8879 1.0000
1.500 0.6084 0.02044 0.01293 -0.1241 0.8773 1.0000
1.750 0.6592 0.02019 0.01267 -0.1279 0.8725 1.0000
2.000 0.6898 0.02029 0.01277 -0.1283 0.8609 1.0000
2.250 0.7241 0.02031 0.01283 -0.1291 0.8509 1.0000
2.500 0.7688 0.01996 0.01253 -0.1315 0.8448 1.0000
2.750 0.7983 0.02004 0.01266 -0.1314 0.8334 1.0000
3.000 0.8325 0.01986 0.01258 -0.1318 0.8227 1.0000
3.250 0.8768 0.01917 0.01197 -0.1334 0.8149 1.0000
3.500 0.9075 0.01893 0.01180 -0.1329 0.8015 1.0000
3.750 0.9376 0.01870 0.01170 -0.1323 0.7878 1.0000
4.000 0.9679 0.01842 0.01152 -0.1316 0.7735 1.0000
4.250 0.9980 0.01810 0.01130 -0.1307 0.7584 1.0000
4.500 1.0278 0.01780 0.01110 -0.1299 0.7427 1.0000
4.750 1.0515 0.01754 0.01098 -0.1279 0.7199 1.0000
5.000 1.0776 0.01683 0.01029 -0.1255 0.6888 1.0000
5.250 1.1002 0.01641 0.00985 -0.1229 0.6499 1.0000
5.500 1.1221 0.01633 0.00974 -0.1205 0.6084 1.0000
5.750 1.1426 0.01651 0.00992 -0.1182 0.5632 1.0000
6.000 1.1586 0.01696 0.01016 -0.1151 0.4936 1.0000
6.250 1.1627 0.01830 0.01067 -0.1104 0.3454 1.0000
6.500 1.1531 0.02169 0.01254 -0.1048 0.1663 1.0000
6.750 1.1587 0.02404 0.01440 -0.1013 0.1173 1.0000
7.000 1.1712 0.02571 0.01594 -0.0987 0.0987 1.0000
7.250 1.1858 0.02743 0.01760 -0.0965 0.0864 1.0000
7.500 1.2041 0.02949 0.01949 -0.0951 0.0768 1.0000
7.750 1.2286 0.03134 0.02151 -0.0941 0.0700 1.0000
8.000 1.2560 0.03410 0.02414 -0.0941 0.0631 1.0000
8.250 1.2842 0.03655 0.02692 -0.0934 0.0599 1.0000
8.500 1.3094 0.03917 0.02979 -0.0927 0.0566 1.0000
8.750 1.3329 0.04270 0.03338 -0.0925 0.0526 1.0000
9.000 1.3517 0.04715 0.03826 -0.0911 0.0517 1.0000
9.250 1.3653 0.05112 0.04272 -0.0890 0.0517 1.0000
9.500 1.3775 0.05627 0.04830 -0.0872 0.0521 1.0000
9.750 1.3847 0.05965 0.05213 -0.0845 0.0524 1.0000
10.000 1.3869 0.06383 0.05674 -0.0817 0.0525 1.0000
10.250 1.3848 0.06782 0.06114 -0.0787 0.0526 1.0000
10.500 1.3408 0.07250 0.06686 -0.0711 0.0580 1.0000
10.750 1.3197 0.07687 0.07150 -0.0675 0.0594 1.0000
11.000 1.2991 0.08135 0.07619 -0.0649 0.0606 1.0000
11.250 1.2807 0.08629 0.08130 -0.0635 0.0617 1.0000
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Polar data table (+)
Polar graphs
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