GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 549 AIRFOIL (goe549-il) Reynolds number: 200,000 Max Cl/Cd: 75.68 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe549-il-200000-n5.txt Download as CSV file: xf-goe549-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2728 0.10376 0.10025 -0.0492 1.0000 0.0279
-10.250 -0.2576 0.10016 0.09665 -0.0515 0.9867 0.0272
-10.000 -0.2441 0.09600 0.09249 -0.0553 0.9726 0.0265
-9.750 -0.2315 0.09089 0.08736 -0.0605 0.9582 0.0258
-9.500 -0.2187 0.08507 0.08152 -0.0669 0.9436 0.0252
-9.250 -0.2064 0.07850 0.07490 -0.0746 0.9293 0.0248
-8.750 -0.2899 0.04317 0.03892 -0.1091 0.8769 0.0231
-8.500 -0.2910 0.03958 0.03501 -0.1098 0.8604 0.0233
-8.250 -0.2837 0.03714 0.03231 -0.1096 0.8458 0.0236
-8.000 -0.2741 0.03492 0.02983 -0.1090 0.8319 0.0240
-7.750 -0.2635 0.03260 0.02719 -0.1082 0.8183 0.0245
-7.500 -0.2502 0.03058 0.02484 -0.1074 0.8049 0.0253
-7.250 -0.2356 0.02860 0.02246 -0.1063 0.7907 0.0264
-7.000 -0.2194 0.02676 0.02013 -0.1051 0.7762 0.0276
-6.750 -0.2007 0.02540 0.01828 -0.1040 0.7617 0.0284
-6.500 -0.1814 0.02355 0.01623 -0.1032 0.7477 0.0292
-6.250 -0.1595 0.02249 0.01498 -0.1025 0.7337 0.0300
-6.000 -0.1366 0.02165 0.01396 -0.1018 0.7204 0.0310
-5.750 -0.1131 0.02095 0.01306 -0.1011 0.7081 0.0325
-5.500 -0.0892 0.02020 0.01205 -0.1005 0.6972 0.0339
-5.250 -0.0645 0.01961 0.01120 -0.0998 0.6874 0.0350
-5.000 -0.0401 0.01881 0.01019 -0.0992 0.6791 0.0360
-4.750 -0.0158 0.01792 0.00922 -0.0987 0.6711 0.0369
-4.500 0.0089 0.01728 0.00848 -0.0981 0.6644 0.0376
-4.250 0.0340 0.01675 0.00788 -0.0976 0.6576 0.0383
-4.000 0.0591 0.01630 0.00733 -0.0971 0.6515 0.0391
-3.750 0.0844 0.01591 0.00687 -0.0966 0.6459 0.0403
-3.500 0.1099 0.01558 0.00647 -0.0962 0.6403 0.0417
-3.250 0.1355 0.01527 0.00606 -0.0957 0.6352 0.0426
-3.000 0.1611 0.01499 0.00570 -0.0953 0.6301 0.0433
-2.750 0.1870 0.01476 0.00540 -0.0949 0.6250 0.0440
-2.500 0.2129 0.01452 0.00508 -0.0945 0.6201 0.0451
-2.250 0.2390 0.01433 0.00481 -0.0941 0.6156 0.0467
-2.000 0.2653 0.01416 0.00461 -0.0938 0.6104 0.0489
-1.750 0.2917 0.01405 0.00442 -0.0935 0.6054 0.0519
-1.500 0.3182 0.01392 0.00427 -0.0932 0.6010 0.0600
-1.250 0.3434 0.01361 0.00418 -0.0928 0.5956 0.1094
-1.000 0.3676 0.01314 0.00409 -0.0924 0.5906 0.2152
-0.750 0.3924 0.01286 0.00406 -0.0920 0.5862 0.3171
-0.500 0.4167 0.01258 0.00410 -0.0914 0.5813 0.4078
-0.250 0.4403 0.01234 0.00418 -0.0906 0.5763 0.5072
0.000 0.4647 0.01222 0.00422 -0.0898 0.5718 0.5812
0.250 0.4880 0.01204 0.00428 -0.0887 0.5675 0.6618
0.500 0.5112 0.01181 0.00435 -0.0875 0.5622 0.7405
0.750 0.5809 0.01149 0.00438 -0.0956 0.5565 0.9579
1.000 0.6241 0.01159 0.00438 -0.0990 0.5512 1.0000
1.250 0.6482 0.01169 0.00442 -0.0983 0.5458 1.0000
1.500 0.6726 0.01180 0.00444 -0.0976 0.5409 1.0000
1.750 0.6971 0.01192 0.00449 -0.0970 0.5360 1.0000
2.000 0.7214 0.01202 0.00456 -0.0963 0.5301 1.0000
2.250 0.7460 0.01214 0.00461 -0.0957 0.5249 1.0000
2.500 0.7706 0.01227 0.00469 -0.0951 0.5195 1.0000
2.750 0.7951 0.01238 0.00479 -0.0944 0.5134 1.0000
3.000 0.8196 0.01251 0.00485 -0.0938 0.5079 1.0000
3.250 0.8440 0.01264 0.00498 -0.0932 0.5014 1.0000
3.500 0.8684 0.01278 0.00508 -0.0925 0.4953 1.0000
3.750 0.8927 0.01293 0.00521 -0.0919 0.4891 1.0000
4.000 0.9168 0.01308 0.00534 -0.0912 0.4821 1.0000
4.250 0.9408 0.01324 0.00546 -0.0905 0.4759 1.0000
4.500 0.9648 0.01341 0.00565 -0.0899 0.4688 1.0000
4.750 0.9884 0.01359 0.00578 -0.0891 0.4623 1.0000
5.000 1.0120 0.01377 0.00599 -0.0884 0.4547 1.0000
5.250 1.0351 0.01398 0.00616 -0.0876 0.4477 1.0000
5.500 1.0584 0.01419 0.00640 -0.0868 0.4404 1.0000
5.750 1.0810 0.01442 0.00661 -0.0860 0.4333 1.0000
6.000 1.1037 0.01465 0.00686 -0.0852 0.4258 1.0000
6.250 1.1258 0.01491 0.00711 -0.0842 0.4186 1.0000
6.500 1.1480 0.01517 0.00739 -0.0834 0.4118 1.0000
6.750 1.1693 0.01545 0.00767 -0.0823 0.4041 1.0000
7.000 1.1898 0.01574 0.00797 -0.0811 0.3950 1.0000
7.250 1.2088 0.01608 0.00827 -0.0797 0.3858 1.0000
7.500 1.2279 0.01639 0.00862 -0.0784 0.3756 1.0000
7.750 1.2464 0.01675 0.00897 -0.0769 0.3669 1.0000
8.000 1.2645 0.01711 0.00934 -0.0754 0.3588 1.0000
8.250 1.2819 0.01749 0.00976 -0.0739 0.3506 1.0000
8.500 1.2978 0.01789 0.01017 -0.0720 0.3432 1.0000
8.750 1.3124 0.01830 0.01061 -0.0700 0.3353 1.0000
9.000 1.3255 0.01876 0.01108 -0.0677 0.3275 1.0000
9.250 1.3400 0.01922 0.01160 -0.0658 0.3206 1.0000
9.500 1.3521 0.01975 0.01215 -0.0635 0.3125 1.0000
9.750 1.3643 0.02031 0.01276 -0.0615 0.3037 1.0000
10.000 1.3734 0.02101 0.01345 -0.0590 0.2942 1.0000
10.250 1.3847 0.02168 0.01418 -0.0571 0.2848 1.0000
10.500 1.3955 0.02242 0.01498 -0.0551 0.2780 1.0000
10.750 1.4068 0.02317 0.01582 -0.0534 0.2704 1.0000
11.000 1.4159 0.02407 0.01677 -0.0515 0.2627 1.0000
11.250 1.4234 0.02510 0.01784 -0.0496 0.2529 1.0000
11.500 1.4296 0.02626 0.01905 -0.0477 0.2416 1.0000
11.750 1.4333 0.02766 0.02047 -0.0458 0.2288 1.0000
12.000 1.4344 0.02931 0.02214 -0.0439 0.2141 1.0000
12.250 1.4314 0.03138 0.02418 -0.0420 0.1965 1.0000
12.500 1.4247 0.03390 0.02664 -0.0403 0.1760 1.0000
12.750 1.4156 0.03682 0.02949 -0.0387 0.1544 1.0000
13.000 1.4011 0.04045 0.03301 -0.0374 0.1295 1.0000
13.250 1.3863 0.04434 0.03681 -0.0365 0.1088 1.0000
13.500 1.3765 0.04790 0.04034 -0.0359 0.0973 1.0000
13.750 1.3677 0.05149 0.04394 -0.0355 0.0891 1.0000
14.000 1.3616 0.05490 0.04741 -0.0352 0.0825 1.0000
14.250 1.3539 0.05859 0.05115 -0.0352 0.0769 1.0000
14.500 1.3511 0.06181 0.05447 -0.0352 0.0704 1.0000
14.750 1.3445 0.06558 0.05830 -0.0354 0.0648 1.0000
15.000 1.3407 0.06910 0.06192 -0.0356 0.0574 1.0000
15.250 1.3341 0.07308 0.06595 -0.0361 0.0505 1.0000
15.500 1.3257 0.07741 0.07031 -0.0368 0.0439 1.0000
15.750 1.3173 0.08183 0.07477 -0.0376 0.0391 1.0000
16.000 1.3102 0.08619 0.07918 -0.0385 0.0360 1.0000
16.250 1.3030 0.09065 0.08371 -0.0395 0.0334 1.0000
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