GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 585 AIRFOIL (goe585-il) Reynolds number: 200,000 Max Cl/Cd: 66.05 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe585-il-200000-n5.txt Download as CSV file: xf-goe585-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 585 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4075 0.08798 0.08434 -0.0288 1.0000 0.0223
-8.500 -0.4132 0.08421 0.08063 -0.0299 1.0000 0.0230
-8.250 -0.4225 0.08058 0.07707 -0.0305 1.0000 0.0235
-8.000 -0.4346 0.07736 0.07395 -0.0304 1.0000 0.0236
-7.750 -0.4440 0.07284 0.06948 -0.0324 1.0000 0.0238
-7.500 -0.4522 0.06796 0.06463 -0.0346 1.0000 0.0240
-7.250 -0.4591 0.06250 0.05915 -0.0369 1.0000 0.0242
-7.000 -0.4601 0.04607 0.04236 -0.0491 0.9963 0.0250
-6.750 -0.4333 0.04412 0.04030 -0.0523 0.9923 0.0260
-6.500 -0.4046 0.04308 0.03918 -0.0545 0.9884 0.0273
-6.250 -0.3814 0.03424 0.02971 -0.0599 0.9826 0.0290
-6.000 -0.3568 0.02806 0.02273 -0.0626 0.9772 0.0310
-5.750 -0.3287 0.02521 0.01925 -0.0638 0.9727 0.0326
-5.500 -0.3017 0.02260 0.01613 -0.0645 0.9677 0.0336
-5.250 -0.2707 0.02088 0.01419 -0.0659 0.9645 0.0351
-5.000 -0.2422 0.01994 0.01312 -0.0663 0.9593 0.0366
-4.750 -0.2116 0.01880 0.01173 -0.0670 0.9548 0.0377
-4.500 -0.1781 0.01772 0.01042 -0.0682 0.9516 0.0386
-4.250 -0.1480 0.01681 0.00934 -0.0686 0.9468 0.0395
-4.000 -0.1171 0.01610 0.00848 -0.0692 0.9416 0.0411
-3.750 -0.0829 0.01541 0.00767 -0.0704 0.9381 0.0423
-3.500 -0.0497 0.01474 0.00690 -0.0714 0.9341 0.0429
-3.250 -0.0210 0.01413 0.00623 -0.0715 0.9273 0.0437
-3.000 0.0123 0.01348 0.00558 -0.0725 0.9227 0.0452
-2.750 0.0436 0.01302 0.00509 -0.0730 0.9145 0.0470
-2.500 0.0800 0.01256 0.00458 -0.0745 0.9057 0.0491
-2.250 0.1111 0.01221 0.00418 -0.0748 0.8925 0.0524
-2.000 0.1415 0.01188 0.00384 -0.0750 0.8794 0.0572
-1.750 0.1712 0.01158 0.00354 -0.0751 0.8657 0.0660
-1.500 0.1998 0.01129 0.00332 -0.0750 0.8522 0.0883
-1.250 0.2280 0.01107 0.00315 -0.0748 0.8390 0.1159
-1.000 0.2558 0.01088 0.00299 -0.0746 0.8248 0.1420
-0.750 0.2830 0.01067 0.00286 -0.0743 0.8092 0.1742
-0.500 0.3096 0.01042 0.00276 -0.0738 0.7926 0.2321
-0.250 0.3352 0.01010 0.00271 -0.0733 0.7752 0.3336
0.000 0.3557 0.00934 0.00266 -0.0718 0.7578 0.5540
0.250 0.4367 0.00848 0.00261 -0.0822 0.7351 1.0000
0.500 0.4611 0.00860 0.00256 -0.0812 0.7142 1.0000
0.750 0.4850 0.00873 0.00253 -0.0801 0.6927 1.0000
1.000 0.5086 0.00887 0.00252 -0.0789 0.6694 1.0000
1.250 0.5319 0.00903 0.00253 -0.0778 0.6450 1.0000
1.500 0.5549 0.00920 0.00256 -0.0765 0.6172 1.0000
1.750 0.5774 0.00940 0.00259 -0.0752 0.5853 1.0000
2.000 0.5992 0.00965 0.00264 -0.0738 0.5465 1.0000
2.250 0.6200 0.00996 0.00272 -0.0722 0.5024 1.0000
2.500 0.6407 0.01032 0.00284 -0.0707 0.4615 1.0000
2.750 0.6621 0.01066 0.00299 -0.0694 0.4309 1.0000
3.000 0.6842 0.01099 0.00317 -0.0682 0.4069 1.0000
3.250 0.7070 0.01130 0.00338 -0.0671 0.3859 1.0000
3.500 0.7298 0.01160 0.00358 -0.0661 0.3671 1.0000
3.750 0.7529 0.01190 0.00380 -0.0651 0.3509 1.0000
4.000 0.7764 0.01218 0.00404 -0.0642 0.3369 1.0000
4.250 0.7999 0.01247 0.00428 -0.0634 0.3245 1.0000
4.500 0.8234 0.01276 0.00454 -0.0625 0.3130 1.0000
5.000 0.8704 0.01335 0.00510 -0.0608 0.2906 1.0000
5.250 0.8940 0.01366 0.00540 -0.0600 0.2810 1.0000
5.500 0.9172 0.01399 0.00572 -0.0591 0.2721 1.0000
5.750 0.9408 0.01429 0.00605 -0.0583 0.2616 1.0000
6.000 0.9638 0.01461 0.00637 -0.0574 0.2496 1.0000
6.250 0.9866 0.01495 0.00670 -0.0566 0.2369 1.0000
6.500 1.0091 0.01531 0.00706 -0.0556 0.2262 1.0000
6.750 1.0324 0.01563 0.00744 -0.0548 0.2175 1.0000
7.000 1.0550 0.01600 0.00784 -0.0539 0.2094 1.0000
7.250 1.0775 0.01637 0.00825 -0.0530 0.2002 1.0000
7.500 1.1000 0.01673 0.00869 -0.0521 0.1901 1.0000
7.750 1.1218 0.01713 0.00913 -0.0511 0.1785 1.0000
8.000 1.1428 0.01757 0.00956 -0.0501 0.1616 1.0000
8.250 1.1628 0.01811 0.01004 -0.0489 0.1416 1.0000
8.500 1.1824 0.01870 0.01059 -0.0478 0.1174 1.0000
8.750 1.1993 0.01954 0.01130 -0.0463 0.0912 1.0000
9.000 1.2154 0.02045 0.01213 -0.0447 0.0731 1.0000
9.250 1.2315 0.02135 0.01301 -0.0430 0.0602 1.0000
9.500 1.2468 0.02226 0.01393 -0.0413 0.0490 1.0000
9.750 1.2611 0.02323 0.01491 -0.0395 0.0382 1.0000
10.000 1.2737 0.02427 0.01596 -0.0374 0.0299 1.0000
10.250 1.2840 0.02534 0.01709 -0.0350 0.0254 1.0000
10.500 1.2929 0.02638 0.01823 -0.0323 0.0223 1.0000
10.750 1.2992 0.02759 0.01950 -0.0295 0.0204 1.0000
11.000 1.3058 0.02877 0.02081 -0.0269 0.0188 1.0000
11.250 1.3114 0.03004 0.02221 -0.0244 0.0176 1.0000
11.500 1.3153 0.03146 0.02376 -0.0219 0.0169 1.0000
11.750 1.3170 0.03311 0.02554 -0.0195 0.0162 1.0000
12.000 1.3152 0.03512 0.02766 -0.0172 0.0155 1.0000
12.250 1.3105 0.03748 0.03016 -0.0152 0.0150 1.0000
12.500 1.3075 0.03992 0.03272 -0.0137 0.0146 1.0000
12.750 1.3065 0.04233 0.03533 -0.0127 0.0143 1.0000
13.000 1.3043 0.04504 0.03821 -0.0120 0.0138 1.0000
13.250 1.3004 0.04813 0.04145 -0.0118 0.0135 1.0000
13.500 1.2962 0.05144 0.04491 -0.0119 0.0131 1.0000
13.750 1.2915 0.05501 0.04863 -0.0125 0.0126 1.0000
14.000 1.2840 0.05915 0.05292 -0.0133 0.0125 1.0000
14.250 1.2770 0.06344 0.05735 -0.0147 0.0123 1.0000
14.500 1.2685 0.06817 0.06223 -0.0164 0.0120 1.0000
14.750 1.2598 0.07315 0.06735 -0.0184 0.0119 1.0000
15.000 1.2511 0.07829 0.07263 -0.0205 0.0118 1.0000
15.250 1.2411 0.08384 0.07830 -0.0230 0.0116 1.0000
15.500 1.2328 0.08920 0.08380 -0.0254 0.0115 1.0000
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Polar data table (+)
Polar graphs
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