GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 613 AIRFOIL (goe613-il) Reynolds number: 200,000 Max Cl/Cd: 72.26 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe613-il-200000.txt Download as CSV file: xf-goe613-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 613 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3726 0.09189 0.08878 -0.0245 1.0000 0.0446
-7.500 -0.3907 0.09057 0.08753 -0.0219 1.0000 0.0451
-7.250 -0.4113 0.08943 0.08647 -0.0190 1.0000 0.0452
-7.000 -0.3847 0.08223 0.07913 -0.0402 0.9905 0.0479
-6.750 -0.3613 0.07427 0.07096 -0.0515 0.9840 0.0486
-6.500 -0.3489 0.07040 0.06723 -0.0494 0.9801 0.0498
-6.250 -0.3266 0.06746 0.06428 -0.0509 0.9752 0.0516
-6.000 -0.2961 0.06315 0.05986 -0.0569 0.9714 0.0546
-5.750 -0.2602 0.05873 0.05476 -0.0669 0.9604 0.0603
-5.500 -0.2383 0.05165 0.04775 -0.0705 0.9579 0.0620
-5.250 -0.2213 0.04932 0.04546 -0.0703 0.9496 0.0638
-5.000 -0.1895 0.04650 0.04252 -0.0735 0.9460 0.0689
-4.750 -0.1662 0.04250 0.03801 -0.0755 0.9381 0.0756
-4.500 -0.1389 0.04004 0.03558 -0.0770 0.9339 0.0784
-4.250 -0.1022 0.03747 0.03247 -0.0801 0.9306 0.0896
-4.000 -0.0832 0.03526 0.03039 -0.0797 0.9236 0.0927
-3.750 -0.0515 0.03331 0.02809 -0.0813 0.9190 0.1054
-3.500 -0.0151 0.03137 0.02610 -0.0837 0.9166 0.1140
-3.250 0.0234 0.02917 0.02375 -0.0866 0.9149 0.1277
-3.000 0.0415 0.02779 0.02227 -0.0852 0.9052 0.1403
-2.750 0.0833 0.02596 0.02030 -0.0885 0.9024 0.1687
-2.250 0.1681 0.01996 0.01263 -0.0881 0.8909 0.0725
-2.000 0.2091 0.01829 0.01079 -0.0901 0.8871 0.0710
-1.750 0.2391 0.01749 0.00985 -0.0901 0.8795 0.0721
-1.500 0.2742 0.01651 0.00878 -0.0909 0.8731 0.0725
-1.250 0.3054 0.01568 0.00791 -0.0911 0.8655 0.0727
-1.000 0.3372 0.01495 0.00714 -0.0913 0.8574 0.0736
-0.750 0.3631 0.01419 0.00640 -0.0905 0.8473 0.0752
-0.500 0.3942 0.01348 0.00574 -0.0908 0.8389 0.0791
-0.250 0.4198 0.01310 0.00536 -0.0899 0.8272 0.0850
0.000 0.4450 0.01271 0.00495 -0.0889 0.8147 0.0904
0.250 0.4713 0.01236 0.00457 -0.0882 0.8019 0.1027
0.500 0.5744 0.00973 0.00431 -0.1037 0.7904 1.0000
0.750 0.5981 0.00970 0.00413 -0.1025 0.7738 1.0000
1.000 0.6221 0.00971 0.00399 -0.1013 0.7562 1.0000
1.250 0.6462 0.00975 0.00386 -0.1002 0.7373 1.0000
1.500 0.6680 0.00984 0.00382 -0.0987 0.7161 1.0000
1.750 0.6900 0.00995 0.00379 -0.0973 0.6940 1.0000
2.000 0.7108 0.01008 0.00380 -0.0956 0.6701 1.0000
2.250 0.7313 0.01024 0.00380 -0.0939 0.6443 1.0000
2.500 0.7510 0.01042 0.00382 -0.0920 0.6163 1.0000
2.750 0.7703 0.01066 0.00388 -0.0901 0.5876 1.0000
3.000 0.7894 0.01095 0.00398 -0.0882 0.5608 1.0000
3.250 0.8089 0.01129 0.00414 -0.0864 0.5369 1.0000
3.500 0.8286 0.01166 0.00434 -0.0848 0.5150 1.0000
3.750 0.8486 0.01203 0.00458 -0.0832 0.4947 1.0000
4.000 0.8686 0.01237 0.00482 -0.0816 0.4748 1.0000
4.250 0.8888 0.01271 0.00507 -0.0801 0.4566 1.0000
4.500 0.9091 0.01305 0.00532 -0.0787 0.4399 1.0000
4.750 0.9299 0.01340 0.00560 -0.0773 0.4249 1.0000
5.000 0.9510 0.01374 0.00588 -0.0761 0.4113 1.0000
5.250 0.9724 0.01409 0.00619 -0.0748 0.3988 1.0000
5.500 0.9939 0.01447 0.00650 -0.0737 0.3875 1.0000
5.750 1.0156 0.01487 0.00683 -0.0726 0.3769 1.0000
6.000 1.0366 0.01519 0.00717 -0.0714 0.3655 1.0000
6.250 1.0570 0.01554 0.00750 -0.0701 0.3536 1.0000
6.500 1.0763 0.01588 0.00781 -0.0686 0.3410 1.0000
6.750 1.0961 0.01625 0.00815 -0.0672 0.3299 1.0000
7.000 1.1162 0.01658 0.00851 -0.0659 0.3201 1.0000
7.250 1.1352 0.01690 0.00886 -0.0644 0.3091 1.0000
7.500 1.1534 0.01724 0.00920 -0.0627 0.2981 1.0000
7.750 1.1722 0.01759 0.00958 -0.0612 0.2889 1.0000
8.000 1.1896 0.01787 0.00995 -0.0594 0.2778 1.0000
8.250 1.2058 0.01817 0.01029 -0.0575 0.2657 1.0000
8.500 1.2192 0.01845 0.01060 -0.0550 0.2507 1.0000
8.750 1.2331 0.01879 0.01098 -0.0526 0.2373 1.0000
9.000 1.2471 0.01918 0.01140 -0.0503 0.2233 1.0000
9.250 1.2580 0.01969 0.01185 -0.0476 0.2010 1.0000
9.500 1.2685 0.02038 0.01243 -0.0450 0.1667 1.0000
9.750 1.2687 0.02182 0.01346 -0.0412 0.1146 1.0000
10.000 1.2579 0.02415 0.01527 -0.0364 0.0489 1.0000
10.250 1.2584 0.02577 0.01681 -0.0331 0.0352 1.0000
10.500 1.2653 0.02698 0.01812 -0.0306 0.0320 1.0000
10.750 1.2710 0.02830 0.01956 -0.0282 0.0300 1.0000
11.000 1.2747 0.02980 0.02118 -0.0257 0.0286 1.0000
11.250 1.2744 0.03162 0.02316 -0.0231 0.0273 1.0000
11.500 1.2744 0.03350 0.02518 -0.0209 0.0266 1.0000
11.750 1.2748 0.03544 0.02728 -0.0190 0.0261 1.0000
12.000 1.2738 0.03760 0.02958 -0.0173 0.0254 1.0000
12.250 1.2706 0.04009 0.03221 -0.0158 0.0248 1.0000
12.500 1.2658 0.04289 0.03515 -0.0146 0.0244 1.0000
12.750 1.2607 0.04588 0.03828 -0.0138 0.0241 1.0000
13.000 1.2546 0.04914 0.04165 -0.0132 0.0239 1.0000
13.250 1.2498 0.05240 0.04502 -0.0128 0.0237 1.0000
13.500 1.2445 0.05586 0.04858 -0.0127 0.0234 1.0000
13.750 1.2420 0.05908 0.05189 -0.0126 0.0233 1.0000
14.000 1.2406 0.06222 0.05511 -0.0125 0.0232 1.0000
14.250 1.2403 0.06522 0.05817 -0.0123 0.0229 1.0000
14.500 1.2431 0.06786 0.06088 -0.0119 0.0227 1.0000
14.750 1.2486 0.07012 0.06321 -0.0112 0.0227 1.0000
15.000 1.2561 0.07219 0.06536 -0.0105 0.0225 1.0000
15.250 1.2658 0.07404 0.06722 -0.0094 0.0220 1.0000
15.500 1.2799 0.07561 0.06883 -0.0078 0.0215 1.0000
15.750 1.2951 0.07773 0.07106 -0.0063 0.0212 1.0000
16.000 1.2972 0.08088 0.07437 -0.0065 0.0213 1.0000
16.250 1.2964 0.08439 0.07807 -0.0071 0.0214 1.0000
16.500 1.2918 0.08831 0.08218 -0.0083 0.0216 1.0000
16.750 1.2863 0.09268 0.08676 -0.0096 0.0217 1.0000
17.000 1.2764 0.09764 0.09196 -0.0116 0.0219 1.0000
17.250 1.2642 0.10328 0.09786 -0.0142 0.0223 1.0000
17.500 1.2486 0.10977 0.10464 -0.0174 0.0228 1.0000
17.750 1.2296 0.11711 0.11225 -0.0215 0.0231 1.0000
18.000 1.2094 0.12503 0.12043 -0.0261 0.0235 1.0000
18.250 1.1892 0.13329 0.12892 -0.0312 0.0239 1.0000
18.500 1.1684 0.14209 0.13793 -0.0368 0.0244 1.0000
18.750 1.1466 0.15153 0.14756 -0.0430 0.0247 1.0000
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