Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Reynolds number: 500,000 Max Cl/Cd: 38.4 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel10-il-500000-n5.txt Download as CSV file: xf-eiffel10-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5364 0.15788 0.15529 0.0173 1.0000 0.0084
-12.750 -0.5289 0.15478 0.15218 0.0159 1.0000 0.0085
-12.500 -0.5212 0.15166 0.14907 0.0146 1.0000 0.0087
-12.250 -0.5135 0.14856 0.14597 0.0132 1.0000 0.0088
-12.000 -0.5058 0.14549 0.14290 0.0119 1.0000 0.0088
-11.750 -0.4979 0.14242 0.13984 0.0105 1.0000 0.0089
-11.500 -0.4900 0.13938 0.13680 0.0092 1.0000 0.0090
-11.250 -0.4821 0.13636 0.13379 0.0078 1.0000 0.0090
-11.000 -0.4741 0.13335 0.13079 0.0065 1.0000 0.0090
-10.750 -0.4661 0.13036 0.12781 0.0051 1.0000 0.0090
-10.500 -0.4580 0.12739 0.12485 0.0038 1.0000 0.0090
-10.250 -0.4498 0.12444 0.12190 0.0024 1.0000 0.0090
-10.000 -0.4416 0.12152 0.11899 0.0010 1.0000 0.0090
-9.750 -0.4332 0.11862 0.11610 -0.0005 1.0000 0.0091
-9.500 -0.4247 0.11575 0.11324 -0.0020 1.0000 0.0091
-9.250 -0.4161 0.11291 0.11042 -0.0035 1.0000 0.0091
-9.000 -0.4075 0.11011 0.10763 -0.0051 1.0000 0.0091
-8.750 -0.3989 0.10736 0.10490 -0.0068 1.0000 0.0091
-8.500 -0.3904 0.10467 0.10223 -0.0084 1.0000 0.0091
-8.000 -0.3732 0.09909 0.09670 -0.0114 1.0000 0.0091
-7.750 -0.3632 0.09590 0.09353 -0.0125 1.0000 0.0092
-7.500 -0.3515 0.09296 0.09061 -0.0144 1.0000 0.0093
-7.250 -0.3386 0.09011 0.08779 -0.0167 1.0000 0.0093
-7.000 -0.3170 0.08676 0.08444 -0.0213 0.9820 0.0095
-6.750 -0.2900 0.08314 0.08074 -0.0269 0.9277 0.0098
-6.500 -0.2736 0.08040 0.07788 -0.0294 0.8923 0.0099
-6.250 -0.2554 0.07759 0.07496 -0.0323 0.8625 0.0100
-6.000 -0.2356 0.07478 0.07199 -0.0355 0.8280 0.0101
-5.750 -0.2134 0.07187 0.06895 -0.0391 0.8006 0.0102
-5.500 -0.1901 0.06905 0.06591 -0.0428 0.7568 0.0104
-5.250 -0.1659 0.06644 0.06289 -0.0466 0.6643 0.0105
-4.750 -0.1130 0.06276 0.05732 -0.0554 0.0252 0.0109
-4.500 -0.0796 0.05969 0.05419 -0.0606 0.0239 0.0110
-4.250 -0.0429 0.05660 0.05105 -0.0664 0.0231 0.0111
-4.000 -0.0026 0.05348 0.04785 -0.0726 0.0226 0.0111
-3.750 0.0395 0.05037 0.04465 -0.0789 0.0223 0.0111
-3.500 0.0715 0.04737 0.04161 -0.0825 0.0218 0.0112
-3.250 0.0966 0.04494 0.03917 -0.0844 0.0197 0.0114
-3.000 0.1301 0.04269 0.03688 -0.0879 0.0187 0.0118
-2.750 0.1671 0.04032 0.03444 -0.0917 0.0181 0.0121
-2.500 0.2047 0.03805 0.03208 -0.0953 0.0174 0.0124
-2.250 0.2427 0.03588 0.02981 -0.0987 0.0170 0.0127
-2.000 0.2812 0.03382 0.02763 -0.1019 0.0166 0.0130
-1.750 0.3215 0.03182 0.02548 -0.1048 0.0164 0.0133
-1.500 0.3616 0.02986 0.02335 -0.1074 0.0163 0.0134
-1.250 0.3999 0.02801 0.02132 -0.1094 0.0164 0.0134
-1.000 0.4368 0.02626 0.01938 -0.1110 0.0164 0.0134
-0.750 0.4676 0.02489 0.01794 -0.1126 0.0166 0.0137
-0.500 0.4990 0.02395 0.01689 -0.1136 0.0169 0.0140
-0.250 0.5314 0.02302 0.01581 -0.1144 0.0173 0.0148
0.250 0.5946 0.02185 0.01409 -0.1151 0.0191 0.0167
0.500 0.6243 0.02167 0.01374 -0.1152 0.0187 0.0174
0.750 0.6566 0.02065 0.01257 -0.1150 0.0172 0.0187
1.250 0.7130 0.02069 0.01216 -0.1150 0.0155 0.0193
1.500 0.7409 0.02108 0.01241 -0.1147 0.0154 0.0196
1.750 0.7693 0.02185 0.01302 -0.1143 0.0153 0.0147
2.000 0.7982 0.02096 0.01235 -0.1137 0.0145 0.0146
2.250 0.8259 0.02151 0.01293 -0.1131 0.0142 0.0150
2.500 0.8534 0.02241 0.01385 -0.1125 0.0141 0.0163
2.750 0.8808 0.02349 0.01505 -0.1119 0.0143 0.0174
3.000 0.9070 0.02639 0.01773 -0.1120 0.0152 0.0174
3.250 0.9336 0.02777 0.01923 -0.1115 0.0152 0.0176
3.500 0.9598 0.02919 0.02080 -0.1109 0.0152 0.0181
3.750 0.9855 0.03069 0.02246 -0.1103 0.0152 0.0191
4.000 1.0106 0.03228 0.02423 -0.1096 0.0152 0.0215
4.250 1.0350 0.03397 0.02609 -0.1088 0.0152 0.0223
4.500 1.0586 0.03578 0.02810 -0.1078 0.0152 0.0237
4.750 1.0814 0.03769 0.03023 -0.1068 0.0152 0.0274
5.000 1.1010 0.03833 0.03256 -0.1055 0.0151 1.0000
5.250 1.1221 0.04053 0.03496 -0.1043 0.0151 1.0000
5.500 1.1423 0.04283 0.03747 -0.1029 0.0151 1.0000
5.750 1.1614 0.04526 0.04012 -0.1015 0.0151 1.0000
6.000 1.1796 0.04783 0.04294 -0.1000 0.0150 1.0000
6.250 1.1967 0.05054 0.04587 -0.0983 0.0150 1.0000
6.500 1.2158 0.05303 0.04867 -0.0962 0.0145 1.0000
6.750 1.2312 0.05597 0.05183 -0.0945 0.0139 1.0000
7.000 1.2429 0.05921 0.05525 -0.0929 0.0135 1.0000
7.250 1.2522 0.06265 0.05888 -0.0912 0.0133 1.0000
7.500 1.2589 0.06622 0.06264 -0.0896 0.0132 1.0000
7.750 1.2628 0.06991 0.06651 -0.0879 0.0130 1.0000
8.000 1.2635 0.07372 0.07048 -0.0861 0.0129 1.0000
8.250 1.2605 0.07763 0.07455 -0.0844 0.0128 1.0000
8.500 1.2531 0.08165 0.07871 -0.0827 0.0127 1.0000
8.750 1.2392 0.08560 0.08279 -0.0807 0.0127 1.0000
9.000 1.2171 0.08966 0.08697 -0.0787 0.0127 1.0000
9.250 1.1936 0.09499 0.09242 -0.0795 0.0127 1.0000
9.500 1.1696 0.10202 0.09957 -0.0831 0.0128 1.0000
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