GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 457 AIRFOIL (goe457-il) Reynolds number: 1,000,000 Max Cl/Cd: 117 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe457-il-1000000.txt Download as CSV file: xf-goe457-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 457 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3799 0.10650 0.10484 -0.0220 1.0000 0.0127
-9.500 -0.3786 0.10330 0.10166 -0.0225 1.0000 0.0127
-9.250 -0.3834 0.09888 0.09726 -0.0228 1.0000 0.0129
-9.000 -0.3822 0.09623 0.09463 -0.0225 1.0000 0.0130
-8.750 -0.3779 0.09456 0.09298 -0.0215 1.0000 0.0132
-8.500 -0.3774 0.09268 0.09112 -0.0205 1.0000 0.0134
-8.250 -0.3803 0.09088 0.08935 -0.0192 1.0000 0.0136
-8.000 -0.3756 0.08794 0.08642 -0.0207 0.9993 0.0138
-7.750 -0.3604 0.08422 0.08271 -0.0252 0.9974 0.0143
-7.500 -0.3439 0.07998 0.07847 -0.0311 0.9946 0.0150
-6.750 -0.2877 0.01866 0.01538 -0.0935 0.9735 0.0159
-6.500 -0.2571 0.01602 0.01231 -0.0952 0.9722 0.0170
-6.250 -0.2213 0.01630 0.01267 -0.0969 0.9714 0.0175
-6.000 -0.1960 0.01630 0.01266 -0.0963 0.9665 0.0180
-5.750 -0.1647 0.01573 0.01201 -0.0971 0.9637 0.0188
-5.500 -0.1332 0.01467 0.01074 -0.0980 0.9612 0.0200
-5.250 -0.0996 0.01419 0.01011 -0.0991 0.9588 0.0208
-5.000 -0.0749 0.01251 0.00820 -0.0989 0.9535 0.0222
-4.750 -0.0458 0.01227 0.00795 -0.0992 0.9488 0.0231
-4.500 -0.0136 0.01183 0.00745 -0.1000 0.9450 0.0241
-4.250 0.0136 0.01127 0.00679 -0.0998 0.9388 0.0250
-4.000 0.0433 0.01090 0.00634 -0.1000 0.9328 0.0260
-3.750 0.0728 0.01079 0.00616 -0.1001 0.9264 0.0268
-3.500 0.0991 0.00962 0.00479 -0.0997 0.9187 0.0278
-3.250 0.1257 0.00886 0.00396 -0.0993 0.9109 0.0289
-3.000 0.1532 0.00854 0.00360 -0.0991 0.9018 0.0300
-2.750 0.1794 0.00821 0.00323 -0.0985 0.8913 0.0307
-2.500 0.2058 0.00791 0.00286 -0.0980 0.8798 0.0313
-2.250 0.2318 0.00764 0.00252 -0.0973 0.8651 0.0319
-2.000 0.2573 0.00742 0.00222 -0.0965 0.8435 0.0327
-1.750 0.2811 0.00734 0.00197 -0.0953 0.7995 0.0338
-1.500 0.3004 0.00752 0.00180 -0.0931 0.7223 0.0344
-1.250 0.3217 0.00769 0.00169 -0.0916 0.6633 0.0348
-1.000 0.3439 0.00781 0.00157 -0.0902 0.6067 0.0353
-0.750 0.3675 0.00785 0.00140 -0.0892 0.5660 0.0364
-0.500 0.3925 0.00788 0.00130 -0.0884 0.5413 0.0379
-0.250 0.4183 0.00788 0.00123 -0.0878 0.5244 0.0405
0.000 0.4443 0.00789 0.00120 -0.0873 0.5106 0.0443
0.250 0.4702 0.00784 0.00120 -0.0868 0.4984 0.0768
0.500 0.4962 0.00780 0.00120 -0.0863 0.4868 0.1115
0.750 0.5215 0.00757 0.00126 -0.0858 0.4762 0.2333
1.000 0.5469 0.00745 0.00132 -0.0853 0.4666 0.3186
1.250 0.5701 0.00703 0.00141 -0.0845 0.4567 0.5364
1.500 0.6258 0.00615 0.00155 -0.0909 0.4417 1.0000
1.750 0.6511 0.00626 0.00159 -0.0902 0.4295 1.0000
2.000 0.6765 0.00637 0.00163 -0.0896 0.4186 1.0000
2.250 0.7016 0.00649 0.00169 -0.0889 0.4051 1.0000
2.500 0.7266 0.00664 0.00175 -0.0882 0.3881 1.0000
2.750 0.7518 0.00678 0.00182 -0.0875 0.3744 1.0000
3.000 0.7770 0.00693 0.00190 -0.0869 0.3628 1.0000
3.250 0.8021 0.00708 0.00199 -0.0862 0.3500 1.0000
3.500 0.8271 0.00725 0.00209 -0.0856 0.3353 1.0000
3.750 0.8521 0.00743 0.00220 -0.0849 0.3209 1.0000
4.000 0.8773 0.00759 0.00231 -0.0843 0.3082 1.0000
4.250 0.9024 0.00777 0.00244 -0.0837 0.2955 1.0000
4.500 0.9275 0.00794 0.00258 -0.0831 0.2831 1.0000
4.750 0.9524 0.00814 0.00272 -0.0824 0.2698 1.0000
5.000 0.9768 0.00839 0.00288 -0.0818 0.2527 1.0000
5.250 1.0009 0.00867 0.00307 -0.0810 0.2335 1.0000
5.500 1.0244 0.00900 0.00329 -0.0802 0.2085 1.0000
5.750 1.0469 0.00944 0.00356 -0.0793 0.1768 1.0000
6.000 1.0669 0.01013 0.00398 -0.0779 0.1276 1.0000
6.250 1.0892 0.01060 0.00434 -0.0770 0.1067 1.0000
6.500 1.1124 0.01096 0.00464 -0.0762 0.0946 1.0000
6.750 1.1356 0.01132 0.00495 -0.0753 0.0838 1.0000
7.000 1.1592 0.01164 0.00523 -0.0746 0.0765 1.0000
7.250 1.1827 0.01195 0.00552 -0.0738 0.0694 1.0000
7.500 1.2053 0.01234 0.00585 -0.0729 0.0603 1.0000
7.750 1.2278 0.01273 0.00618 -0.0721 0.0512 1.0000
8.000 1.2452 0.01360 0.00682 -0.0704 0.0208 1.0000
8.250 1.2654 0.01420 0.00741 -0.0691 0.0148 1.0000
8.500 1.2866 0.01467 0.00796 -0.0679 0.0135 1.0000
8.750 1.3068 0.01521 0.00857 -0.0666 0.0123 1.0000
9.000 1.3256 0.01588 0.00932 -0.0651 0.0111 1.0000
9.250 1.3460 0.01635 0.00984 -0.0638 0.0107 1.0000
9.500 1.3653 0.01689 0.01045 -0.0625 0.0102 1.0000
9.750 1.3838 0.01748 0.01110 -0.0610 0.0097 1.0000
10.000 1.4007 0.01815 0.01184 -0.0592 0.0092 1.0000
10.250 1.4158 0.01892 0.01268 -0.0572 0.0088 1.0000
10.500 1.4216 0.02029 0.01418 -0.0538 0.0082 1.0000
10.750 1.4311 0.02111 0.01509 -0.0508 0.0081 1.0000
11.000 1.4431 0.02174 0.01579 -0.0483 0.0079 1.0000
11.250 1.4529 0.02250 0.01663 -0.0456 0.0077 1.0000
11.500 1.4636 0.02323 0.01742 -0.0431 0.0075 1.0000
11.750 1.4734 0.02403 0.01830 -0.0406 0.0071 1.0000
12.000 1.4790 0.02510 0.01945 -0.0378 0.0069 1.0000
12.250 1.4854 0.02616 0.02059 -0.0352 0.0067 1.0000
12.500 1.4893 0.02743 0.02194 -0.0326 0.0066 1.0000
12.750 1.4908 0.02894 0.02355 -0.0300 0.0065 1.0000
13.000 1.4942 0.03040 0.02509 -0.0279 0.0063 1.0000
13.250 1.4901 0.03256 0.02735 -0.0255 0.0061 1.0000
13.500 1.4859 0.03493 0.02983 -0.0237 0.0061 1.0000
13.750 1.4730 0.03840 0.03343 -0.0222 0.0059 1.0000
14.000 1.4569 0.04272 0.03788 -0.0217 0.0058 1.0000
14.250 1.4425 0.04735 0.04264 -0.0220 0.0058 1.0000
14.500 1.4340 0.05161 0.04703 -0.0229 0.0057 1.0000
14.750 1.4324 0.05524 0.05077 -0.0241 0.0056 1.0000
15.000 1.4245 0.05980 0.05545 -0.0255 0.0056 1.0000
15.250 1.4194 0.06416 0.05993 -0.0271 0.0056 1.0000
15.500 1.4087 0.06924 0.06511 -0.0289 0.0056 1.0000
15.750 1.4033 0.07382 0.06980 -0.0308 0.0055 1.0000
16.000 1.3913 0.07926 0.07535 -0.0327 0.0055 1.0000
16.250 1.3810 0.08461 0.08080 -0.0349 0.0055 1.0000
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