GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 645 AIRFOIL (goe645-il) Reynolds number: 100,000 Max Cl/Cd: 48.7 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe645-il-100000-n5.txt Download as CSV file: xf-goe645-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 645 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6545 0.04760 0.04190 -0.0766 1.0000 0.0504
-10.500 -0.6647 0.04531 0.03951 -0.0754 0.9980 0.0509
-10.250 -0.6411 0.04208 0.03606 -0.0801 0.9868 0.0523
-10.000 -0.6189 0.03889 0.03255 -0.0839 0.9750 0.0536
-9.750 -0.5958 0.03607 0.02935 -0.0866 0.9631 0.0552
-9.500 -0.5699 0.03376 0.02671 -0.0889 0.9524 0.0569
-9.250 -0.5390 0.03232 0.02527 -0.0907 0.9434 0.0586
-9.000 -0.5115 0.03086 0.02369 -0.0919 0.9324 0.0603
-8.750 -0.4789 0.02927 0.02189 -0.0939 0.9245 0.0624
-8.500 -0.4513 0.02789 0.02030 -0.0947 0.9129 0.0647
-8.250 -0.4216 0.02689 0.01930 -0.0957 0.9024 0.0671
-8.000 -0.3896 0.02582 0.01812 -0.0970 0.8929 0.0700
-7.750 -0.3620 0.02482 0.01695 -0.0973 0.8808 0.0729
-7.500 -0.3307 0.02403 0.01613 -0.0983 0.8707 0.0765
-7.250 -0.3017 0.02326 0.01520 -0.0987 0.8590 0.0817
-7.000 -0.2739 0.02261 0.01451 -0.0989 0.8471 0.0875
-6.750 -0.2436 0.02188 0.01364 -0.0994 0.8369 0.0956
-6.500 -0.2178 0.02127 0.01289 -0.0990 0.8242 0.1060
-6.250 -0.1908 0.02072 0.01221 -0.0989 0.8128 0.1181
-6.000 -0.1627 0.02021 0.01164 -0.0989 0.8022 0.1305
-5.750 -0.1375 0.01985 0.01124 -0.0984 0.7897 0.1416
-5.500 -0.1100 0.01955 0.01085 -0.0982 0.7788 0.1533
-5.250 -0.0827 0.01930 0.01050 -0.0979 0.7676 0.1648
-5.000 -0.0566 0.01915 0.01027 -0.0974 0.7559 0.1766
-4.750 -0.0288 0.01905 0.01009 -0.0971 0.7455 0.1894
-4.500 -0.0032 0.01899 0.01000 -0.0965 0.7336 0.2019
-4.250 0.0233 0.01895 0.00987 -0.0960 0.7226 0.2149
-4.000 0.0503 0.01886 0.00963 -0.0955 0.7119 0.2276
-3.750 0.0758 0.01877 0.00952 -0.0948 0.7003 0.2369
-3.500 0.1029 0.01861 0.00922 -0.0943 0.6903 0.2467
-3.250 0.1285 0.01852 0.00906 -0.0936 0.6787 0.2562
-3.000 0.1547 0.01843 0.00887 -0.0931 0.6680 0.2658
-2.750 0.1813 0.01836 0.00868 -0.0925 0.6578 0.2758
-2.500 0.2069 0.01830 0.00857 -0.0919 0.6468 0.2850
-2.250 0.2338 0.01826 0.00838 -0.0914 0.6374 0.2955
-2.000 0.2591 0.01820 0.00831 -0.0907 0.6264 0.3042
-1.750 0.2856 0.01818 0.00817 -0.0902 0.6170 0.3140
-1.500 0.3115 0.01813 0.00808 -0.0896 0.6071 0.3220
-1.250 0.3377 0.01811 0.00799 -0.0890 0.5978 0.3309
-1.000 0.3637 0.01808 0.00790 -0.0885 0.5887 0.3395
-0.750 0.3896 0.01810 0.00786 -0.0879 0.5795 0.3510
-0.500 0.4155 0.01809 0.00784 -0.0873 0.5709 0.3626
-0.250 0.4411 0.01810 0.00783 -0.0867 0.5619 0.3748
0.000 0.4671 0.01811 0.00777 -0.0862 0.5530 0.3868
0.250 0.4921 0.01810 0.00778 -0.0855 0.5428 0.3979
0.750 0.5433 0.01812 0.00774 -0.0843 0.5233 0.4212
1.000 0.5696 0.01814 0.00771 -0.0838 0.5152 0.4340
1.250 0.5947 0.01818 0.00782 -0.0832 0.5063 0.4502
1.500 0.6209 0.01821 0.00785 -0.0827 0.4994 0.4716
1.750 0.6456 0.01824 0.00802 -0.0820 0.4916 0.5008
2.000 0.6702 0.01822 0.00812 -0.0813 0.4847 0.5466
2.250 0.6933 0.01804 0.00824 -0.0802 0.4781 0.6336
2.500 0.7526 0.01767 0.00844 -0.0861 0.4675 1.0000
2.750 0.7762 0.01792 0.00856 -0.0852 0.4600 1.0000
3.000 0.7988 0.01816 0.00872 -0.0842 0.4514 1.0000
3.250 0.8224 0.01842 0.00884 -0.0833 0.4444 1.0000
3.500 0.8445 0.01868 0.00908 -0.0823 0.4360 1.0000
3.750 0.8678 0.01894 0.00920 -0.0814 0.4290 1.0000
4.000 0.8898 0.01924 0.00950 -0.0803 0.4214 1.0000
4.250 0.9123 0.01952 0.00972 -0.0793 0.4145 1.0000
4.500 0.9350 0.01983 0.00997 -0.0784 0.4082 1.0000
4.750 0.9566 0.02015 0.01029 -0.0773 0.4010 1.0000
5.000 0.9790 0.02045 0.01051 -0.0764 0.3948 1.0000
5.250 0.9997 0.02080 0.01088 -0.0752 0.3874 1.0000
5.500 1.0206 0.02112 0.01117 -0.0740 0.3803 1.0000
5.750 1.0411 0.02148 0.01150 -0.0728 0.3733 1.0000
6.000 1.0605 0.02183 0.01186 -0.0714 0.3656 1.0000
6.250 1.0806 0.02219 0.01216 -0.0701 0.3592 1.0000
6.500 1.0993 0.02260 0.01263 -0.0687 0.3521 1.0000
6.750 1.1185 0.02299 0.01299 -0.0674 0.3463 1.0000
7.000 1.1371 0.02343 0.01345 -0.0660 0.3404 1.0000
7.250 1.1552 0.02389 0.01394 -0.0646 0.3347 1.0000
7.500 1.1735 0.02433 0.01437 -0.0631 0.3300 1.0000
7.750 1.1909 0.02484 0.01491 -0.0617 0.3251 1.0000
8.000 1.2066 0.02535 0.01549 -0.0599 0.3200 1.0000
8.250 1.2218 0.02585 0.01600 -0.0581 0.3155 1.0000
8.500 1.2368 0.02638 0.01653 -0.0563 0.3111 1.0000
8.750 1.2495 0.02701 0.01725 -0.0543 0.3059 1.0000
9.000 1.2627 0.02762 0.01790 -0.0524 0.3013 1.0000
9.250 1.2774 0.02821 0.01847 -0.0507 0.2975 1.0000
9.500 1.2889 0.02898 0.01934 -0.0488 0.2929 1.0000
9.750 1.2998 0.02977 0.02022 -0.0469 0.2883 1.0000
10.000 1.3119 0.03053 0.02101 -0.0453 0.2844 1.0000
10.250 1.3255 0.03127 0.02174 -0.0438 0.2809 1.0000
10.500 1.3324 0.03237 0.02299 -0.0419 0.2761 1.0000
10.750 1.3402 0.03344 0.02416 -0.0402 0.2715 1.0000
11.000 1.3500 0.03442 0.02516 -0.0387 0.2675 1.0000
11.250 1.3594 0.03551 0.02630 -0.0373 0.2636 1.0000
11.500 1.3634 0.03701 0.02796 -0.0358 0.2593 1.0000
11.750 1.3686 0.03848 0.02953 -0.0344 0.2551 1.0000
12.000 1.3763 0.03978 0.03086 -0.0332 0.2511 1.0000
12.250 1.3833 0.04121 0.03234 -0.0322 0.2472 1.0000
12.500 1.3819 0.04340 0.03473 -0.0310 0.2428 1.0000
12.750 1.3823 0.04549 0.03693 -0.0301 0.2383 1.0000
13.000 1.3882 0.04712 0.03860 -0.0293 0.2341 1.0000
13.250 1.3890 0.04931 0.04087 -0.0286 0.2298 1.0000
13.500 1.3801 0.05259 0.04433 -0.0282 0.2247 1.0000
13.750 1.3778 0.05525 0.04708 -0.0278 0.2199 1.0000
14.000 1.3879 0.05655 0.04834 -0.0272 0.2157 1.0000
14.250 1.3671 0.06161 0.05367 -0.0277 0.2102 1.0000
14.500 1.3577 0.06548 0.05765 -0.0280 0.2050 1.0000
14.750 1.3648 0.06728 0.05945 -0.0278 0.2008 1.0000
15.000 1.3438 0.07303 0.06539 -0.0290 0.1955 1.0000
15.250 1.3282 0.07824 0.07074 -0.0302 0.1904 1.0000
15.500 1.3321 0.08070 0.07324 -0.0304 0.1870 1.0000
15.750 1.3203 0.08560 0.07824 -0.0316 0.1830 1.0000
16.000 1.2801 0.09516 0.08801 -0.0349 0.1776 1.0000
16.250 1.2771 0.09897 0.09188 -0.0359 0.1745 1.0000
16.500 1.2886 0.10043 0.09337 -0.0359 0.1727 1.0000
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