GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 549 AIRFOIL (goe549-il) Reynolds number: 500,000 Max Cl/Cd: 100.8 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe549-il-500000-n5.txt Download as CSV file: xf-goe549-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 549 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5324 0.03131 0.02769 -0.1159 0.8868 0.0144
-10.750 -0.5420 0.02797 0.02391 -0.1142 0.8690 0.0145
-10.500 -0.5302 0.02677 0.02254 -0.1130 0.8561 0.0147
-10.250 -0.5125 0.02614 0.02181 -0.1122 0.8451 0.0148
-10.000 -0.4969 0.02514 0.02063 -0.1111 0.8345 0.0150
-9.750 -0.4782 0.02449 0.01986 -0.1103 0.8231 0.0151
-9.500 -0.4591 0.02380 0.01903 -0.1094 0.8111 0.0154
-9.250 -0.4403 0.02298 0.01805 -0.1085 0.7992 0.0156
-9.000 -0.4217 0.02202 0.01689 -0.1076 0.7862 0.0159
-8.750 -0.4027 0.02106 0.01571 -0.1066 0.7718 0.0164
-8.500 -0.3840 0.01989 0.01427 -0.1055 0.7548 0.0171
-8.250 -0.3649 0.01872 0.01276 -0.1043 0.7343 0.0179
-8.000 -0.3438 0.01811 0.01194 -0.1033 0.7108 0.0184
-7.750 -0.3209 0.01781 0.01151 -0.1026 0.6898 0.0187
-7.500 -0.2974 0.01757 0.01115 -0.1019 0.6732 0.0191
-7.250 -0.2736 0.01727 0.01071 -0.1013 0.6606 0.0196
-6.750 -0.2252 0.01647 0.00964 -0.1002 0.6427 0.0210
-6.500 -0.2005 0.01608 0.00909 -0.0997 0.6358 0.0217
-6.250 -0.1752 0.01575 0.00863 -0.0992 0.6299 0.0223
-6.000 -0.1501 0.01532 0.00808 -0.0988 0.6242 0.0228
-5.750 -0.1259 0.01478 0.00749 -0.0983 0.6193 0.0235
-5.500 -0.1002 0.01448 0.00715 -0.0979 0.6149 0.0242
-5.250 -0.0741 0.01422 0.00685 -0.0976 0.6104 0.0250
-5.000 -0.0480 0.01400 0.00657 -0.0973 0.6060 0.0260
-4.750 -0.0219 0.01380 0.00629 -0.0970 0.6020 0.0270
-4.500 0.0047 0.01358 0.00601 -0.0967 0.5983 0.0277
-4.250 0.0311 0.01332 0.00569 -0.0964 0.5943 0.0281
-4.000 0.0574 0.01305 0.00536 -0.0961 0.5904 0.0283
-3.750 0.0821 0.01255 0.00481 -0.0955 0.5868 0.0288
-3.500 0.1077 0.01217 0.00440 -0.0951 0.5833 0.0293
-3.250 0.1338 0.01187 0.00407 -0.0948 0.5794 0.0298
-3.000 0.1601 0.01163 0.00381 -0.0945 0.5753 0.0303
-2.750 0.1864 0.01146 0.00359 -0.0941 0.5712 0.0311
-2.500 0.2131 0.01128 0.00338 -0.0939 0.5672 0.0318
-2.250 0.2400 0.01111 0.00319 -0.0936 0.5627 0.0324
-2.000 0.2668 0.01098 0.00302 -0.0934 0.5584 0.0331
-1.750 0.2936 0.01088 0.00287 -0.0931 0.5546 0.0337
-1.500 0.3208 0.01077 0.00274 -0.0929 0.5507 0.0344
-1.250 0.3481 0.01069 0.00263 -0.0928 0.5465 0.0351
-1.000 0.3752 0.01062 0.00252 -0.0925 0.5423 0.0361
-0.750 0.4020 0.01056 0.00242 -0.0923 0.5385 0.0385
-0.500 0.4293 0.01047 0.00236 -0.0921 0.5343 0.0419
-0.250 0.4555 0.01023 0.00230 -0.0919 0.5297 0.0961
0.000 0.4804 0.00986 0.00225 -0.0915 0.5254 0.2053
0.250 0.5056 0.00960 0.00225 -0.0911 0.5213 0.3056
0.750 0.5565 0.00918 0.00231 -0.0904 0.5112 0.4694
1.000 0.5814 0.00906 0.00237 -0.0898 0.5068 0.5458
1.250 0.6074 0.00898 0.00242 -0.0894 0.5017 0.5933
1.500 0.6320 0.00887 0.00248 -0.0888 0.4959 0.6535
1.750 0.6547 0.00871 0.00254 -0.0876 0.4906 0.7307
2.250 0.7606 0.00845 0.00275 -0.0984 0.4765 0.9992
2.500 0.7865 0.00854 0.00281 -0.0980 0.4699 1.0000
2.750 0.8105 0.00867 0.00287 -0.0972 0.4631 1.0000
3.000 0.8353 0.00877 0.00295 -0.0966 0.4570 1.0000
3.250 0.8596 0.00890 0.00303 -0.0959 0.4500 1.0000
3.500 0.8838 0.00903 0.00312 -0.0952 0.4429 1.0000
3.750 0.9076 0.00919 0.00323 -0.0945 0.4338 1.0000
4.000 0.9308 0.00937 0.00334 -0.0936 0.4212 1.0000
4.250 0.9543 0.00954 0.00347 -0.0929 0.4120 1.0000
4.500 0.9769 0.00976 0.00362 -0.0919 0.3994 1.0000
4.750 1.0001 0.00997 0.00378 -0.0911 0.3888 1.0000
5.000 1.0235 0.01016 0.00394 -0.0903 0.3802 1.0000
5.250 1.0463 0.01038 0.00412 -0.0895 0.3720 1.0000
5.500 1.0688 0.01062 0.00431 -0.0886 0.3604 1.0000
5.750 1.0904 0.01089 0.00453 -0.0875 0.3484 1.0000
6.000 1.1121 0.01116 0.00475 -0.0865 0.3394 1.0000
6.250 1.1345 0.01139 0.00497 -0.0856 0.3309 1.0000
6.500 1.1555 0.01167 0.00522 -0.0845 0.3211 1.0000
6.750 1.1764 0.01196 0.00548 -0.0834 0.3122 1.0000
7.000 1.1970 0.01225 0.00574 -0.0822 0.3021 1.0000
7.250 1.2167 0.01257 0.00604 -0.0809 0.2937 1.0000
7.500 1.2378 0.01281 0.00630 -0.0799 0.2878 1.0000
7.750 1.2566 0.01314 0.00660 -0.0784 0.2806 1.0000
8.000 1.2752 0.01341 0.00689 -0.0769 0.2735 1.0000
8.250 1.2903 0.01379 0.00724 -0.0748 0.2641 1.0000
8.500 1.3072 0.01411 0.00758 -0.0731 0.2565 1.0000
8.750 1.3217 0.01453 0.00798 -0.0710 0.2469 1.0000
9.000 1.3346 0.01504 0.00845 -0.0687 0.2343 1.0000
9.250 1.3475 0.01557 0.00896 -0.0666 0.2227 1.0000
9.500 1.3601 0.01614 0.00951 -0.0644 0.2108 1.0000
9.750 1.3726 0.01674 0.01010 -0.0624 0.2006 1.0000
10.000 1.3811 0.01756 0.01087 -0.0600 0.1851 1.0000
10.250 1.3856 0.01865 0.01187 -0.0572 0.1661 1.0000
10.500 1.3838 0.02017 0.01327 -0.0541 0.1386 1.0000
10.750 1.3684 0.02269 0.01555 -0.0499 0.0976 1.0000
11.000 1.3687 0.02440 0.01721 -0.0477 0.0845 1.0000
11.250 1.3732 0.02593 0.01875 -0.0460 0.0776 1.0000
11.500 1.3816 0.02723 0.02011 -0.0448 0.0728 1.0000
11.750 1.3878 0.02877 0.02168 -0.0435 0.0679 1.0000
12.000 1.3933 0.03044 0.02338 -0.0424 0.0629 1.0000
12.250 1.3950 0.03249 0.02544 -0.0412 0.0539 1.0000
12.500 1.3923 0.03505 0.02797 -0.0401 0.0417 1.0000
12.750 1.3865 0.03803 0.03092 -0.0391 0.0309 1.0000
13.000 1.3850 0.04070 0.03362 -0.0384 0.0263 1.0000
13.250 1.3851 0.04329 0.03626 -0.0379 0.0237 1.0000
13.500 1.3860 0.04584 0.03887 -0.0375 0.0220 1.0000
13.750 1.3865 0.04847 0.04156 -0.0371 0.0209 1.0000
14.000 1.3871 0.05114 0.04431 -0.0369 0.0199 1.0000
14.250 1.3881 0.05380 0.04705 -0.0367 0.0190 1.0000
14.500 1.3875 0.05667 0.05001 -0.0365 0.0181 1.0000
14.750 1.3863 0.05970 0.05310 -0.0365 0.0173 1.0000
15.000 1.3847 0.06283 0.05632 -0.0365 0.0168 1.0000
15.250 1.3827 0.06605 0.05963 -0.0367 0.0165 1.0000
15.500 1.3800 0.06945 0.06310 -0.0369 0.0158 1.0000
15.750 1.3798 0.07257 0.06631 -0.0372 0.0154 1.0000
16.000 1.3786 0.07589 0.06972 -0.0376 0.0152 1.0000
16.250 1.3764 0.07936 0.07329 -0.0381 0.0148 1.0000
16.500 1.3743 0.08288 0.07690 -0.0386 0.0143 1.0000
16.750 1.3714 0.08658 0.08067 -0.0393 0.0139 1.0000
17.000 1.3683 0.09033 0.08452 -0.0400 0.0137 1.0000
17.250 1.3642 0.09429 0.08856 -0.0409 0.0132 1.0000
17.500 1.3590 0.09844 0.09278 -0.0419 0.0128 1.0000
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