EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Reynolds number: 500,000 Max Cl/Cd: 96.07 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e818-il-500000-n5.txt Download as CSV file: xf-e818-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 818 HYDROFOIL 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3912 0.08269 0.08040 -0.0636 0.9875 0.0102
-9.000 -0.3860 0.07544 0.07314 -0.0695 0.9849 0.0102
-8.750 -0.3821 0.06749 0.06513 -0.0783 0.9822 0.0102
-8.500 -0.3847 0.06047 0.05803 -0.0866 0.9756 0.0102
-8.250 -0.3843 0.05382 0.05122 -0.0975 0.9692 0.0102
-8.000 -0.3831 0.04887 0.04607 -0.1050 0.9597 0.0102
-7.750 -0.3692 0.04384 0.04074 -0.1116 0.9563 0.0103
-7.500 -0.3580 0.04006 0.03668 -0.1142 0.9501 0.0103
-7.250 -0.3402 0.03618 0.03247 -0.1170 0.9462 0.0103
-7.000 -0.3177 0.03251 0.02846 -0.1196 0.9436 0.0103
-6.750 -0.3077 0.02511 0.02062 -0.1209 0.9375 0.0088
-6.500 -0.2842 0.01984 0.01473 -0.1211 0.9338 0.0053
-6.250 -0.2534 0.01868 0.01334 -0.1213 0.9319 0.0040
-6.000 -0.2244 0.01725 0.01176 -0.1220 0.9302 0.0035
-5.750 -0.2014 0.01510 0.00934 -0.1215 0.9265 0.0033
-5.500 -0.1758 0.01365 0.00774 -0.1215 0.9235 0.0031
-5.250 -0.1482 0.01242 0.00637 -0.1219 0.9210 0.0029
-5.000 -0.1188 0.01142 0.00521 -0.1227 0.9190 0.0028
-4.750 -0.0884 0.01065 0.00427 -0.1235 0.9172 0.0028
-4.500 -0.0611 0.01016 0.00362 -0.1236 0.9143 0.0027
-4.250 -0.0328 0.00982 0.00314 -0.1239 0.9118 0.0027
-4.000 -0.0040 0.00958 0.00277 -0.1242 0.9097 0.0028
-3.750 0.0252 0.00941 0.00251 -0.1246 0.9078 0.0031
-3.500 0.0546 0.00928 0.00228 -0.1250 0.9061 0.0033
-3.250 0.0846 0.00834 0.00184 -0.1264 0.9045 0.1570
-3.000 0.1123 0.00795 0.00172 -0.1269 0.9021 0.2310
-2.500 0.1687 0.00726 0.00170 -0.1281 0.8978 0.4020
-2.250 0.1974 0.00721 0.00167 -0.1285 0.8958 0.4151
-2.000 0.2264 0.00716 0.00162 -0.1289 0.8939 0.4279
-1.750 0.2556 0.00712 0.00160 -0.1293 0.8923 0.4405
-1.500 0.2847 0.00709 0.00159 -0.1298 0.8907 0.4539
-1.000 0.3400 0.00705 0.00165 -0.1300 0.8856 0.4794
-0.750 0.3684 0.00702 0.00167 -0.1302 0.8831 0.4927
-0.500 0.3972 0.00700 0.00170 -0.1305 0.8809 0.5059
0.000 0.4537 0.00696 0.00179 -0.1309 0.8751 0.5333
0.250 0.4812 0.00693 0.00184 -0.1309 0.8709 0.5472
0.500 0.5100 0.00690 0.00187 -0.1312 0.8667 0.5612
0.750 0.5372 0.00688 0.00200 -0.1310 0.8612 0.5748
1.000 0.5649 0.00684 0.00206 -0.1310 0.8547 0.5884
1.250 0.5918 0.00681 0.00212 -0.1307 0.8464 0.6019
1.500 0.6181 0.00675 0.00213 -0.1302 0.8320 0.6155
1.750 0.6427 0.00669 0.00207 -0.1292 0.8007 0.6288
2.000 0.6603 0.00695 0.00197 -0.1265 0.6927 0.6419
2.250 0.6503 0.00922 0.00269 -0.1191 0.3734 0.6527
2.500 0.6563 0.01115 0.00342 -0.1156 0.0996 0.6652
2.750 0.6755 0.01210 0.00408 -0.1140 0.0061 0.6790
3.000 0.7003 0.01244 0.00459 -0.1133 0.0055 0.6940
3.250 0.7242 0.01290 0.00523 -0.1124 0.0053 0.7090
3.500 0.7476 0.01339 0.00585 -0.1115 0.0047 0.7244
3.750 0.7722 0.01367 0.00618 -0.1110 0.0033 0.7405
4.250 0.8123 0.01565 0.00845 -0.1079 0.0020 0.7730
4.500 0.8353 0.01621 0.00914 -0.1069 0.0018 0.7911
4.750 0.8573 0.01720 0.01030 -0.1056 0.0016 0.8098
5.000 0.8799 0.01861 0.01192 -0.1043 0.0014 0.8293
5.500 0.9283 0.02264 0.01653 -0.1016 0.0013 0.8745
5.750 0.9485 0.02516 0.01953 -0.0992 0.0013 0.9067
6.000 0.9662 0.02810 0.02290 -0.0963 0.0013 1.0000
6.250 0.9854 0.03184 0.02703 -0.0939 0.0014 1.0000
6.500 1.0007 0.03589 0.03148 -0.0911 0.0014 1.0000
6.750 1.0123 0.04013 0.03608 -0.0880 0.0015 1.0000
7.000 1.0205 0.04454 0.04083 -0.0847 0.0016 1.0000
7.250 1.0250 0.04908 0.04569 -0.0813 0.0017 1.0000
7.500 1.0251 0.05382 0.05071 -0.0778 0.0018 1.0000
7.750 1.0186 0.05880 0.05596 -0.0741 0.0019 1.0000
8.000 1.0016 0.06377 0.06113 -0.0703 0.0020 1.0000
8.250 0.9979 0.06696 0.06449 -0.0675 0.0020 1.0000
8.500 0.9900 0.06973 0.06738 -0.0642 0.0020 1.0000
8.750 0.9788 0.07284 0.07061 -0.0613 0.0021 1.0000
9.000 0.9652 0.07649 0.07438 -0.0592 0.0021 1.0000
9.250 0.9513 0.08059 0.07858 -0.0583 0.0021 1.0000
9.500 0.9373 0.08530 0.08339 -0.0587 0.0021 1.0000
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Polar data table (+)
Polar graphs
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