GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 647 AIRFOIL (goe647-il) Reynolds number: 100,000 Max Cl/Cd: 41.51 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe647-il-100000.txt Download as CSV file: xf-goe647-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 647 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1132 0.09944 0.09539 -0.0542 0.9613 0.1578
-8.750 -0.0806 0.09513 0.09106 -0.0571 0.9562 0.1630
-8.500 -0.1298 0.09285 0.08884 -0.0659 0.9437 0.1708
-8.250 -0.0606 0.08633 0.08225 -0.0651 0.9418 0.1743
-8.000 -0.0330 0.08201 0.07790 -0.0696 0.9380 0.1829
-7.750 -0.1500 0.09027 0.08604 -0.0582 0.9547 0.1758
-7.000 -0.2191 0.06025 0.05557 -0.0922 0.9067 0.1274
-6.750 -0.2307 0.05060 0.04544 -0.0950 0.8934 0.1090
-6.500 -0.2257 0.04114 0.03475 -0.0991 0.8866 0.1017
-6.250 -0.2169 0.03857 0.03153 -0.0971 0.8732 0.1005
-6.000 -0.1741 0.03528 0.02783 -0.1004 0.8693 0.1010
-5.750 -0.1546 0.03372 0.02612 -0.0993 0.8572 0.1025
-5.500 -0.1088 0.03171 0.02395 -0.1022 0.8521 0.1063
-5.250 -0.0845 0.03034 0.02230 -0.1013 0.8406 0.1089
-5.000 -0.0419 0.02849 0.02000 -0.1030 0.8342 0.1120
-4.750 -0.0157 0.02709 0.01860 -0.1024 0.8233 0.1156
-4.500 0.0238 0.02576 0.01718 -0.1037 0.8160 0.1232
-4.250 0.0487 0.02479 0.01620 -0.1027 0.8050 0.1300
-4.000 0.0855 0.02358 0.01495 -0.1034 0.7973 0.1415
-3.750 0.1077 0.02298 0.01444 -0.1020 0.7855 0.1563
-3.500 0.1431 0.02207 0.01364 -0.1025 0.7778 0.1875
-3.250 0.1621 0.02174 0.01351 -0.1005 0.7652 0.2265
-3.000 0.1938 0.02117 0.01307 -0.1003 0.7570 0.2857
-2.750 0.2146 0.02108 0.01304 -0.0986 0.7443 0.3256
-2.500 0.2387 0.02100 0.01297 -0.0972 0.7329 0.3589
-2.250 0.2696 0.02076 0.01264 -0.0969 0.7232 0.3915
-2.000 0.2910 0.02071 0.01264 -0.0952 0.7100 0.4149
-1.750 0.3181 0.02051 0.01238 -0.0944 0.6987 0.4385
-1.500 0.3475 0.02019 0.01198 -0.0939 0.6875 0.4618
-1.250 0.3703 0.02005 0.01180 -0.0925 0.6739 0.4851
-1.000 0.3963 0.01975 0.01155 -0.0916 0.6616 0.5115
-0.750 0.4264 0.01934 0.01110 -0.0913 0.6502 0.5446
-0.500 0.4485 0.01912 0.01098 -0.0898 0.6358 0.5796
-0.250 0.4735 0.01881 0.01084 -0.0887 0.6221 0.6262
0.000 0.5017 0.01836 0.01063 -0.0879 0.6093 0.7067
0.250 0.6226 0.01780 0.01031 -0.1051 0.5862 1.0000
0.500 0.6453 0.01799 0.01018 -0.1042 0.5735 1.0000
0.750 0.6684 0.01818 0.01010 -0.1031 0.5607 1.0000
1.000 0.6873 0.01848 0.01024 -0.1014 0.5471 1.0000
1.250 0.7091 0.01877 0.01032 -0.1002 0.5352 1.0000
1.500 0.7340 0.01901 0.01032 -0.0994 0.5246 1.0000
1.750 0.7526 0.01938 0.01061 -0.0977 0.5128 1.0000
2.000 0.7773 0.01969 0.01069 -0.0969 0.5034 1.0000
2.250 0.7976 0.02004 0.01095 -0.0955 0.4929 1.0000
2.500 0.8206 0.02043 0.01118 -0.0945 0.4841 1.0000
2.750 0.8425 0.02081 0.01146 -0.0933 0.4752 1.0000
3.000 0.8669 0.02124 0.01174 -0.0927 0.4678 1.0000
3.250 0.8868 0.02171 0.01219 -0.0913 0.4597 1.0000
3.500 0.9156 0.02209 0.01233 -0.0913 0.4534 1.0000
3.750 0.9318 0.02268 0.01298 -0.0894 0.4457 1.0000
4.000 0.9562 0.02309 0.01328 -0.0888 0.4391 1.0000
4.250 0.9809 0.02363 0.01372 -0.0883 0.4334 1.0000
4.500 0.9982 0.02427 0.01441 -0.0866 0.4270 1.0000
4.750 1.0233 0.02476 0.01481 -0.0861 0.4217 1.0000
5.000 1.0506 0.02538 0.01529 -0.0861 0.4172 1.0000
5.250 1.0643 0.02617 0.01623 -0.0840 0.4117 1.0000
5.500 1.0855 0.02678 0.01683 -0.0830 0.4067 1.0000
5.750 1.1144 0.02729 0.01720 -0.0832 0.4024 1.0000
6.000 1.1317 0.02815 0.01813 -0.0818 0.3979 1.0000
6.250 1.1456 0.02904 0.01914 -0.0798 0.3932 1.0000
6.500 1.1662 0.02979 0.01990 -0.0789 0.3892 1.0000
6.750 1.1930 0.03044 0.02048 -0.0789 0.3857 1.0000
7.000 1.2152 0.03142 0.02145 -0.0783 0.3825 1.0000
7.250 1.2198 0.03273 0.02299 -0.0752 0.3788 1.0000
7.500 1.2316 0.03385 0.02422 -0.0731 0.3750 1.0000
7.750 1.2508 0.03470 0.02509 -0.0721 0.3714 1.0000
8.000 1.2782 0.03539 0.02573 -0.0723 0.3683 1.0000
8.250 1.2969 0.03662 0.02698 -0.0714 0.3655 1.0000
8.500 1.2846 0.03870 0.02936 -0.0665 0.3625 1.0000
8.750 1.2740 0.04086 0.03174 -0.0620 0.3595 1.0000
9.000 1.2672 0.04292 0.03394 -0.0582 0.3567 1.0000
9.250 1.2743 0.04441 0.03549 -0.0561 0.3542 1.0000
9.500 1.3032 0.04516 0.03623 -0.0565 0.3516 1.0000
9.750 1.3435 0.04591 0.03690 -0.0585 0.3491 1.0000
10.750 0.6539 0.13633 0.12857 -0.0618 0.3749 1.0000
11.000 0.6714 0.13849 0.13073 -0.0618 0.3706 1.0000
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Polar data table (+)
Polar graphs
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