GOE 419 AIRFOIL (goe419-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 419 AIRFOIL (goe419-il) Reynolds number: 200,000 Max Cl/Cd: 78.54 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe419-il-200000-n5.txt Download as CSV file: xf-goe419-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 419 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3599 0.09091 0.08764 -0.0230 1.0000 0.0143
-7.250 -0.3635 0.08876 0.08556 -0.0221 1.0000 0.0146
-7.000 -0.3633 0.08626 0.08311 -0.0222 1.0000 0.0149
-6.750 -0.3625 0.08373 0.08064 -0.0226 1.0000 0.0153
-6.500 -0.3622 0.08127 0.07823 -0.0228 1.0000 0.0156
-6.250 -0.3406 0.07708 0.07403 -0.0287 0.9964 0.0165
-6.000 -0.3112 0.07232 0.06923 -0.0364 0.9907 0.0176
-5.750 -0.2731 0.06780 0.06463 -0.0462 0.9840 0.0196
-5.500 -0.2331 0.06323 0.05994 -0.0554 0.9774 0.0202
-5.250 -0.2000 0.05872 0.05532 -0.0613 0.9706 0.0203
-5.000 -0.1703 0.05439 0.05088 -0.0657 0.9630 0.0204
-4.500 -0.1170 0.04347 0.03969 -0.0727 0.9492 0.0102
-4.250 -0.0819 0.03879 0.03480 -0.0771 0.9446 0.0094
-4.000 -0.0493 0.03450 0.03027 -0.0800 0.9375 0.0088
-3.750 -0.0122 0.02999 0.02543 -0.0830 0.9330 0.0092
-3.500 0.0257 0.02564 0.02067 -0.0851 0.9291 0.0105
-3.250 0.0591 0.02152 0.01602 -0.0863 0.9232 0.0106
-3.000 0.0952 0.01781 0.01161 -0.0877 0.9192 0.0108
-2.750 0.1295 0.01479 0.00789 -0.0885 0.9142 0.0115
-2.500 0.1640 0.01339 0.00615 -0.0897 0.9074 0.0160
-2.250 0.1996 0.01204 0.00453 -0.0910 0.8999 0.0216
-2.000 0.2360 0.01152 0.00388 -0.0927 0.8901 0.0404
-1.750 0.2683 0.01111 0.00339 -0.0936 0.8787 0.0558
-1.500 0.2991 0.01083 0.00294 -0.0942 0.8678 0.0646
-1.250 0.3287 0.01056 0.00262 -0.0945 0.8581 0.0793
-1.000 0.3577 0.01029 0.00236 -0.0948 0.8483 0.1072
-0.750 0.3840 0.01007 0.00221 -0.0946 0.8371 0.1623
-0.500 0.4099 0.00982 0.00214 -0.0943 0.8261 0.2495
-0.250 0.4641 0.00808 0.00207 -0.1003 0.8177 1.0000
0.000 0.4900 0.00815 0.00201 -0.0998 0.8054 1.0000
0.250 0.5155 0.00823 0.00196 -0.0992 0.7924 1.0000
0.500 0.5406 0.00831 0.00195 -0.0986 0.7785 1.0000
0.750 0.5654 0.00839 0.00196 -0.0979 0.7638 1.0000
1.000 0.5902 0.00847 0.00201 -0.0972 0.7480 1.0000
1.250 0.6149 0.00856 0.00205 -0.0965 0.7309 1.0000
1.500 0.6396 0.00867 0.00210 -0.0958 0.7127 1.0000
1.750 0.6643 0.00880 0.00218 -0.0951 0.6946 1.0000
2.000 0.6889 0.00894 0.00233 -0.0943 0.6764 1.0000
2.250 0.7134 0.00911 0.00249 -0.0936 0.6591 1.0000
2.500 0.7359 0.00937 0.00266 -0.0924 0.6282 1.0000
2.750 0.7515 0.00993 0.00280 -0.0896 0.5400 1.0000
3.000 0.7576 0.01123 0.00313 -0.0854 0.3620 1.0000
3.250 0.7561 0.01417 0.00441 -0.0808 0.0234 1.0000
3.500 0.7782 0.01475 0.00516 -0.0795 0.0155 1.0000
3.750 0.7979 0.01565 0.00632 -0.0778 0.0131 1.0000
4.000 0.8186 0.01637 0.00721 -0.0764 0.0112 1.0000
4.250 0.8371 0.01730 0.00825 -0.0746 0.0094 1.0000
4.500 0.8535 0.01851 0.00953 -0.0725 0.0089 1.0000
4.750 0.8703 0.01988 0.01097 -0.0704 0.0085 1.0000
5.000 0.8891 0.02153 0.01266 -0.0685 0.0083 1.0000
5.250 0.9113 0.02334 0.01450 -0.0673 0.0080 1.0000
5.500 0.9352 0.02564 0.01694 -0.0664 0.0066 1.0000
5.750 0.9604 0.02732 0.01883 -0.0654 0.0061 1.0000
6.000 0.9851 0.02992 0.02167 -0.0644 0.0063 1.0000
6.250 1.0071 0.03330 0.02535 -0.0632 0.0068 1.0000
16.250 0.9870 0.21927 0.21575 -0.1016 0.0100 1.0000
16.500 0.9933 0.22335 0.21982 -0.1037 0.0097 1.0000
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Polar data table (+)
Polar graphs
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