Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Reynolds number: 1,000,000 Max Cl/Cd: 45.24 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel10-il-1000000-n5.txt Download as CSV file: xf-eiffel10-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 10 (Wright) - 1903 Wright Flyer 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5480 0.16059 0.15875 0.0196 1.0000 0.0064
-13.000 -0.5404 0.15750 0.15567 0.0182 1.0000 0.0065
-12.750 -0.5329 0.15439 0.15256 0.0169 1.0000 0.0067
-12.500 -0.5252 0.15123 0.14940 0.0155 1.0000 0.0069
-12.250 -0.5176 0.14808 0.14625 0.0142 1.0000 0.0071
-12.000 -0.5101 0.14495 0.14312 0.0129 1.0000 0.0071
-11.750 -0.5023 0.14183 0.14000 0.0116 1.0000 0.0072
-11.500 -0.4945 0.13874 0.13692 0.0102 1.0000 0.0072
-11.250 -0.4867 0.13569 0.13387 0.0089 1.0000 0.0072
-11.000 -0.4788 0.13265 0.13083 0.0076 1.0000 0.0072
-10.750 -0.4708 0.12963 0.12782 0.0062 1.0000 0.0072
-10.500 -0.4626 0.12663 0.12483 0.0048 1.0000 0.0073
-10.250 -0.4544 0.12365 0.12185 0.0035 1.0000 0.0073
-10.000 -0.4462 0.12070 0.11891 0.0021 1.0000 0.0073
-9.750 -0.4379 0.11775 0.11597 0.0007 1.0000 0.0073
-9.500 -0.4295 0.11484 0.11306 -0.0007 1.0000 0.0073
-9.250 -0.4209 0.11193 0.11016 -0.0021 1.0000 0.0073
-9.000 -0.4122 0.10904 0.10729 -0.0036 1.0000 0.0073
-8.750 -0.4035 0.10619 0.10444 -0.0051 1.0000 0.0073
-8.500 -0.3948 0.10335 0.10162 -0.0067 1.0000 0.0073
-8.250 -0.3864 0.10058 0.09887 -0.0082 1.0000 0.0073
-8.000 -0.3775 0.09782 0.09613 -0.0100 1.0000 0.0073
-7.750 -0.3563 0.09402 0.09228 -0.0153 0.9467 0.0073
-7.500 -0.3493 0.09146 0.08948 -0.0153 0.8798 0.0074
-7.250 -0.3364 0.08876 0.08665 -0.0173 0.8462 0.0075
-7.000 -0.3208 0.08598 0.08377 -0.0201 0.8219 0.0075
-6.750 -0.3034 0.08317 0.08086 -0.0232 0.7974 0.0076
-6.500 -0.2848 0.08041 0.07792 -0.0265 0.7529 0.0078
-6.250 -0.2646 0.07765 0.07492 -0.0301 0.6948 0.0079
-6.000 -0.2454 0.07690 0.07235 -0.0339 0.0258 0.0081
-5.750 -0.2218 0.07390 0.06932 -0.0380 0.0225 0.0084
-5.500 -0.1965 0.07085 0.06625 -0.0423 0.0211 0.0086
-5.250 -0.1696 0.06777 0.06314 -0.0468 0.0200 0.0087
-5.000 -0.1408 0.06469 0.06004 -0.0515 0.0190 0.0088
-4.750 -0.1103 0.06160 0.05692 -0.0563 0.0187 0.0089
-4.500 -0.0778 0.05852 0.05379 -0.0613 0.0184 0.0089
-4.250 -0.0436 0.05544 0.05067 -0.0664 0.0182 0.0090
-4.000 -0.0075 0.05236 0.04753 -0.0716 0.0174 0.0090
-3.750 0.0310 0.04926 0.04435 -0.0770 0.0164 0.0091
-3.500 0.0732 0.04607 0.04106 -0.0829 0.0158 0.0091
-3.250 0.1141 0.04319 0.03808 -0.0879 0.0152 0.0091
-2.750 0.1778 0.03826 0.03304 -0.0939 0.0140 0.0093
-2.500 0.2119 0.03630 0.03102 -0.0968 0.0134 0.0096
-2.250 0.2484 0.03427 0.02891 -0.0999 0.0132 0.0098
-2.000 0.2856 0.03226 0.02680 -0.1029 0.0129 0.0100
-1.750 0.3226 0.03035 0.02480 -0.1055 0.0128 0.0102
-1.500 0.3596 0.02855 0.02288 -0.1078 0.0128 0.0105
-1.250 0.3977 0.02677 0.02097 -0.1099 0.0128 0.0109
-0.250 0.5416 0.02047 0.01398 -0.1149 0.0133 0.0111
0.250 0.6034 0.01883 0.01202 -0.1164 0.0126 0.0117
0.750 0.6620 0.01873 0.01144 -0.1160 0.0120 0.0134
1.000 0.6901 0.01907 0.01161 -0.1158 0.0119 0.0134
1.500 0.7498 0.01763 0.01002 -0.1159 0.0116 0.0109
1.750 0.7780 0.01768 0.01002 -0.1156 0.0113 0.0110
2.000 0.8060 0.01791 0.01024 -0.1152 0.0109 0.0113
2.250 0.8334 0.01842 0.01080 -0.1147 0.0104 0.0117
2.500 0.8607 0.01905 0.01147 -0.1143 0.0100 0.0122
2.750 0.8877 0.01981 0.01226 -0.1138 0.0098 0.0132
3.000 0.9148 0.02062 0.01313 -0.1134 0.0096 0.0137
3.250 0.9418 0.02167 0.01427 -0.1129 0.0096 0.0140
3.500 0.9686 0.02312 0.01586 -0.1122 0.0096 0.0144
3.750 0.9956 0.02557 0.01857 -0.1110 0.0101 0.0152
4.000 1.0211 0.02769 0.02089 -0.1100 0.0107 0.0159
4.250 1.0443 0.02993 0.02330 -0.1093 0.0115 0.0175
4.500 1.0656 0.03268 0.02614 -0.1088 0.0117 0.0183
4.750 1.0882 0.03484 0.02846 -0.1079 0.0118 0.0194
5.000 1.1101 0.03705 0.03084 -0.1068 0.0118 0.0208
5.250 1.1311 0.03937 0.03334 -0.1057 0.0118 0.0242
5.750 1.1690 0.04302 0.03883 -0.1034 0.0118 1.0000
7.500 1.1909 0.05773 0.05500 -0.0817 0.0117 1.0000
7.750 1.1900 0.06202 0.05945 -0.0792 0.0117 1.0000
8.000 1.1849 0.06633 0.06391 -0.0766 0.0117 1.0000
8.250 1.1744 0.07064 0.06837 -0.0737 0.0116 1.0000
8.500 1.1540 0.07438 0.07223 -0.0698 0.0116 1.0000
8.750 1.1254 0.07820 0.07615 -0.0663 0.0116 1.0000
9.000 1.0950 0.08302 0.08108 -0.0648 0.0116 1.0000
9.250 1.0642 0.08886 0.08702 -0.0652 0.0117 1.0000
9.500 1.0330 0.09585 0.09410 -0.0674 0.0117 1.0000
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