GOE 451 AIRFOIL (modified line 6) (goe451-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 451 AIRFOIL (modified line 6) (goe451-il) Reynolds number: 200,000 Max Cl/Cd: 50.73 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe451-il-200000.txt Download as CSV file: xf-goe451-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 451 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.4133 0.09402 0.09065 -0.0277 1.0000 0.0175
-7.000 -0.4101 0.08910 0.08577 -0.0255 1.0000 0.0181
-6.750 -0.4040 0.08561 0.08231 -0.0257 0.9997 0.0185
-6.500 -0.3912 0.08188 0.07859 -0.0283 0.9975 0.0191
-6.250 -0.3777 0.07836 0.07509 -0.0312 0.9955 0.0199
-6.000 -0.3625 0.07479 0.07153 -0.0346 0.9938 0.0207
-5.750 -0.3460 0.07132 0.06807 -0.0381 0.9926 0.0216
-5.500 -0.3273 0.06773 0.06442 -0.0420 0.9915 0.0227
-5.250 -0.3018 0.06425 0.06091 -0.0472 0.9900 0.0264
-5.000 -0.2411 0.06227 0.05873 -0.0608 0.9877 0.0289
-4.750 -0.2108 0.05830 0.05468 -0.0654 0.9863 0.0290
-4.500 -0.1740 0.05385 0.05010 -0.0711 0.9833 0.0291
-4.250 -0.1325 0.04910 0.04518 -0.0773 0.9764 0.0292
-4.000 -0.0956 0.04118 0.03719 -0.0844 0.9680 0.0301
-3.750 -0.0507 0.03594 0.03178 -0.0910 0.9361 0.0312
-3.500 0.0223 0.03027 0.02534 -0.1027 0.8090 0.0328
-3.250 0.0492 0.02795 0.02218 -0.1032 0.6879 0.0339
-3.000 0.0601 0.02842 0.02040 -0.1009 0.0631 0.0347
-2.750 0.0910 0.02572 0.01736 -0.1020 0.0499 0.0356
-2.250 0.1537 0.02056 0.01124 -0.1026 0.0358 0.0258
-2.000 0.1818 0.01890 0.00927 -0.1025 0.0313 0.0252
-1.750 0.2106 0.01764 0.00752 -0.1023 0.0301 0.0276
-1.500 0.2369 0.01610 0.00571 -0.1025 0.0245 0.0449
-1.250 0.2618 0.01536 0.00496 -0.1027 0.0218 0.0682
-1.000 0.2873 0.01465 0.00424 -0.1025 0.0193 0.0652
-0.750 0.3107 0.01462 0.00426 -0.1021 0.0154 0.0636
-0.500 0.3364 0.01426 0.00387 -0.1021 0.0129 0.0631
-0.250 0.3602 0.01439 0.00395 -0.1019 0.0120 0.0640
0.000 0.3821 0.01491 0.00434 -0.1014 0.0113 0.0667
0.750 0.4480 0.01787 0.00720 -0.1006 0.0106 0.2730
1.000 0.4657 0.01666 0.00743 -0.0989 0.0106 1.0000
1.250 0.4899 0.01702 0.00771 -0.0990 0.0105 1.0000
1.500 0.5140 0.01740 0.00802 -0.0990 0.0105 1.0000
1.750 0.5380 0.01780 0.00837 -0.0990 0.0105 1.0000
2.000 0.5619 0.01813 0.00866 -0.0991 0.0104 1.0000
2.250 0.5855 0.01788 0.00848 -0.0989 0.0101 1.0000
2.500 0.6095 0.01823 0.00882 -0.0988 0.0088 1.0000
2.750 0.6341 0.01938 0.01001 -0.0988 0.0083 1.0000
3.000 0.6591 0.02105 0.01158 -0.0991 0.0078 1.0000
3.250 0.6850 0.02486 0.01519 -0.0999 0.0075 1.0000
3.750 0.7118 0.01403 0.00500 -0.0947 0.0072 1.0000
4.000 0.7351 0.01454 0.00570 -0.0942 0.0071 1.0000
4.250 0.7580 0.01520 0.00655 -0.0936 0.0071 1.0000
4.500 0.7805 0.01604 0.00759 -0.0930 0.0070 1.0000
4.750 0.8025 0.01696 0.00874 -0.0924 0.0069 1.0000
5.000 0.8241 0.01829 0.01047 -0.0916 0.0067 1.0000
5.250 0.8452 0.01972 0.01220 -0.0909 0.0065 1.0000
5.500 0.8653 0.02149 0.01431 -0.0901 0.0061 1.0000
5.750 0.8840 0.02360 0.01687 -0.0894 0.0058 1.0000
6.000 0.9083 0.02746 0.02012 -0.0903 0.0055 0.1770
6.250 0.9229 0.03053 0.02385 -0.0898 0.0052 0.2214
6.500 0.9345 0.03425 0.02826 -0.0893 0.0050 0.2862
6.750 0.9443 0.03905 0.03342 -0.0884 0.0049 0.2717
7.000 0.9524 0.04438 0.03904 -0.0872 0.0047 0.2399
7.250 0.9587 0.05075 0.04556 -0.0858 0.0046 0.1774
8.500 1.0757 0.07586 0.07058 -0.0875 0.0044 1.0000
8.750 1.0838 0.07696 0.07205 -0.0854 0.0044 1.0000
9.000 1.0913 0.07842 0.07383 -0.0834 0.0043 1.0000
9.250 1.0977 0.08032 0.07603 -0.0815 0.0043 1.0000
9.500 1.1024 0.08272 0.07868 -0.0797 0.0043 1.0000
9.750 1.1050 0.08554 0.08171 -0.0782 0.0042 1.0000
10.000 1.1045 0.08873 0.08510 -0.0767 0.0042 1.0000
10.250 1.1011 0.09211 0.08865 -0.0754 0.0041 1.0000
10.500 1.0941 0.09566 0.09235 -0.0742 0.0041 1.0000
10.750 1.0814 0.09897 0.09578 -0.0725 0.0041 1.0000
11.000 1.0663 0.10259 0.09950 -0.0716 0.0041 1.0000
11.250 1.0514 0.10683 0.10383 -0.0722 0.0041 1.0000
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Polar data table (+)
Polar graphs
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