EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.17 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e818-il-1000000-n5.txt Download as CSV file: xf-e818-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3185 0.10438 0.10275 -0.0587 0.9909 0.0041
-11.250 -0.3204 0.09915 0.09753 -0.0606 0.9897 0.0043
-11.000 -0.3192 0.09434 0.09272 -0.0626 0.9884 0.0043
-10.750 -0.3182 0.08926 0.08764 -0.0647 0.9870 0.0044
-10.500 -0.3179 0.08402 0.08241 -0.0671 0.9857 0.0045
-10.250 -0.3180 0.07837 0.07677 -0.0698 0.9844 0.0046
-10.000 -0.3189 0.07203 0.07044 -0.0728 0.9831 0.0046
-9.750 -0.3214 0.06450 0.06292 -0.0764 0.9819 0.0045
-9.500 -0.3299 0.05463 0.05300 -0.0808 0.9795 0.0043
-9.250 -0.3350 0.04808 0.04639 -0.0850 0.9742 0.0041
-9.000 -0.3390 0.04140 0.03963 -0.0915 0.9703 0.0040
-8.750 -0.3386 0.03623 0.03435 -0.0981 0.9655 0.0039
-8.500 -0.3409 0.03025 0.02820 -0.1081 0.9587 0.0039
-8.250 -0.3489 0.02475 0.02240 -0.1168 0.9449 0.0040
-8.000 -0.3505 0.02055 0.01790 -0.1191 0.9334 0.0041
-7.750 -0.3499 0.01659 0.01365 -0.1199 0.9239 0.0045
-7.250 -0.3218 0.01266 0.00931 -0.1205 0.9125 0.0055
-7.000 -0.3030 0.01112 0.00758 -0.1208 0.9082 0.0063
-6.750 -0.2818 0.00977 0.00601 -0.1209 0.9048 0.0074
-6.500 -0.2578 0.00892 0.00501 -0.1209 0.9018 0.0089
-6.250 -0.2298 0.00939 0.00540 -0.1206 0.8989 0.0102
-6.000 -0.2066 0.00796 0.00367 -0.1207 0.8959 0.0103
-5.500 -0.1585 0.01200 0.00696 -0.1252 0.8965 0.0042
-5.250 -0.1328 0.01056 0.00539 -0.1251 0.8936 0.0030
-5.000 -0.1053 0.00944 0.00409 -0.1253 0.8912 0.0025
-4.750 -0.0772 0.00871 0.00319 -0.1256 0.8887 0.0022
-4.500 -0.0487 0.00825 0.00260 -0.1258 0.8865 0.0020
-4.250 -0.0201 0.00797 0.00222 -0.1261 0.8843 0.0019
-4.000 0.0085 0.00778 0.00194 -0.1264 0.8823 0.0019
-3.750 0.0371 0.00763 0.00172 -0.1267 0.8805 0.0019
-3.500 0.0658 0.00752 0.00153 -0.1270 0.8787 0.0018
-3.250 0.0942 0.00741 0.00139 -0.1273 0.8767 0.0020
-3.000 0.1225 0.00732 0.00129 -0.1275 0.8747 0.0027
-2.750 0.1509 0.00723 0.00124 -0.1278 0.8728 0.0037
-2.500 0.1801 0.00584 0.00090 -0.1295 0.8709 0.3105
-2.250 0.2088 0.00563 0.00087 -0.1300 0.8691 0.3660
-2.000 0.2375 0.00559 0.00084 -0.1304 0.8673 0.3769
-1.750 0.2663 0.00555 0.00082 -0.1307 0.8656 0.3887
-1.500 0.2948 0.00551 0.00082 -0.1310 0.8637 0.4011
-1.250 0.3231 0.00547 0.00082 -0.1312 0.8613 0.4125
-1.000 0.3515 0.00543 0.00082 -0.1315 0.8585 0.4241
-0.750 0.3799 0.00540 0.00082 -0.1317 0.8554 0.4368
-0.500 0.4084 0.00538 0.00083 -0.1320 0.8518 0.4487
-0.250 0.4361 0.00535 0.00085 -0.1320 0.8468 0.4600
0.000 0.4641 0.00532 0.00086 -0.1321 0.8415 0.4724
0.250 0.4920 0.00530 0.00088 -0.1322 0.8358 0.4850
0.500 0.5195 0.00529 0.00090 -0.1322 0.8269 0.4976
0.750 0.5472 0.00527 0.00101 -0.1322 0.8196 0.5110
1.000 0.5732 0.00528 0.00102 -0.1318 0.8001 0.5243
1.250 0.5960 0.00541 0.00103 -0.1306 0.7460 0.5369
1.500 0.6048 0.00641 0.00132 -0.1266 0.5790 0.5478
1.750 0.6170 0.00751 0.00174 -0.1238 0.4107 0.5591
2.000 0.6259 0.00911 0.00230 -0.1206 0.1598 0.5701
2.250 0.6443 0.01005 0.00273 -0.1191 0.0236 0.5821
2.500 0.6692 0.01039 0.00305 -0.1185 0.0041 0.5951
2.750 0.6951 0.01061 0.00341 -0.1181 0.0037 0.6078
3.000 0.7203 0.01093 0.00382 -0.1176 0.0026 0.6209
3.250 0.7443 0.01139 0.00442 -0.1168 0.0020 0.6341
3.500 0.7700 0.01160 0.00467 -0.1165 0.0018 0.6483
3.750 0.7952 0.01189 0.00503 -0.1161 0.0016 0.6626
4.000 0.8199 0.01224 0.00546 -0.1156 0.0013 0.6770
4.250 0.8438 0.01270 0.00602 -0.1148 0.0010 0.6912
4.500 0.8669 0.01328 0.00672 -0.1139 0.0008 0.7055
4.750 0.8893 0.01399 0.00755 -0.1128 0.0007 0.7203
5.000 0.9114 0.01486 0.00856 -0.1117 0.0007 0.7357
5.250 0.9336 0.01595 0.00982 -0.1105 0.0007 0.7516
5.500 0.9567 0.01743 0.01156 -0.1093 0.0006 0.7674
5.750 0.9818 0.02042 0.01492 -0.1080 0.0007 0.7826
6.000 1.0049 0.02743 0.02266 -0.1045 0.0009 0.7957
6.250 1.0200 0.03271 0.02847 -0.1007 0.0011 0.8112
6.500 1.0305 0.03762 0.03383 -0.0968 0.0013 0.8291
6.750 1.0352 0.04287 0.03952 -0.0925 0.0016 0.8487
7.000 1.0228 0.05004 0.04717 -0.0868 0.0019 0.8705
7.250 1.0228 0.05397 0.05141 -0.0829 0.0019 0.9065
7.500 1.0182 0.05743 0.05513 -0.0783 0.0020 1.0000
7.750 1.0165 0.06168 0.05957 -0.0753 0.0020 1.0000
8.000 1.0115 0.06587 0.06391 -0.0722 0.0020 1.0000
8.250 1.0024 0.06984 0.06803 -0.0691 0.0020 1.0000
8.500 0.9865 0.07314 0.07144 -0.0652 0.0020 1.0000
8.750 0.9693 0.07678 0.07518 -0.0623 0.0020 1.0000
9.000 0.9518 0.08095 0.07946 -0.0608 0.0020 1.0000
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Polar data table (+)
Polar graphs
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