EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Reynolds number: 100,000 Max Cl/Cd: 66.08 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e818-il-100000.txt Download as CSV file: xf-e818-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4663 0.10672 0.10201 -0.0362 1.0000 0.1026
-9.000 -0.4757 0.10421 0.09959 -0.0360 1.0000 0.1076
-8.750 -0.5198 0.10273 0.09830 -0.0392 1.0000 0.1101
-5.750 -0.5477 0.04118 0.03476 -0.0582 1.0000 0.0433
-5.500 -0.5174 0.03689 0.02948 -0.0594 1.0000 0.0344
-5.250 -0.4918 0.03354 0.02587 -0.0598 1.0000 0.0315
-5.000 -0.4637 0.03034 0.02224 -0.0604 1.0000 0.0292
-4.750 -0.4357 0.02786 0.01938 -0.0603 1.0000 0.0274
-4.500 -0.4086 0.02587 0.01713 -0.0598 1.0000 0.0262
-4.250 -0.3821 0.02422 0.01523 -0.0593 1.0000 0.0258
-4.000 -0.3549 0.02283 0.01376 -0.0593 1.0000 0.0262
-3.750 -0.3255 0.02163 0.01237 -0.0600 1.0000 0.0279
-3.500 -0.2951 0.02068 0.01111 -0.0607 1.0000 0.0316
-3.250 -0.2515 0.01759 0.00986 -0.0658 1.0000 0.3906
-3.000 -0.2374 0.01888 0.01163 -0.0620 1.0000 0.5341
-2.750 -0.2139 0.01882 0.01140 -0.0612 1.0000 0.5528
-2.500 -0.1896 0.01878 0.01121 -0.0607 1.0000 0.5733
-2.250 -0.1669 0.01878 0.01114 -0.0599 1.0000 0.5919
-2.000 -0.1432 0.01878 0.01094 -0.0594 1.0000 0.6130
-1.750 -0.1213 0.01882 0.01097 -0.0584 1.0000 0.6321
-1.500 -0.0987 0.01888 0.01099 -0.0577 1.0000 0.6531
-1.250 -0.0773 0.01895 0.01107 -0.0567 1.0000 0.6730
-1.000 -0.0558 0.01904 0.01117 -0.0558 1.0000 0.6943
-0.750 -0.0345 0.01915 0.01130 -0.0549 1.0000 0.7164
-0.500 -0.0149 0.01926 0.01146 -0.0536 1.0000 0.7380
-0.250 0.0047 0.01938 0.01158 -0.0523 1.0000 0.7614
0.000 0.0237 0.01951 0.01175 -0.0509 1.0000 0.7866
0.250 0.0415 0.01963 0.01193 -0.0492 1.0000 0.8136
0.500 0.0573 0.01972 0.01210 -0.0471 1.0000 0.8449
0.750 0.0700 0.01971 0.01221 -0.0444 1.0000 0.8850
1.000 0.0809 0.01917 0.01185 -0.0422 1.0000 1.0000
1.250 0.1167 0.01967 0.01226 -0.0457 1.0000 1.0000
1.500 0.1472 0.02020 0.01270 -0.0479 1.0000 1.0000
1.750 0.1745 0.02075 0.01320 -0.0493 1.0000 1.0000
2.000 0.2076 0.02148 0.01392 -0.0518 0.9965 1.0000
2.250 0.2529 0.02244 0.01491 -0.0564 0.9863 1.0000
2.500 0.2966 0.02334 0.01587 -0.0606 0.9760 1.0000
2.750 0.3396 0.02413 0.01690 -0.0644 0.9654 1.0000
3.000 0.3842 0.02490 0.01782 -0.0684 0.9550 1.0000
3.250 0.4270 0.02549 0.01859 -0.0719 0.9433 1.0000
3.500 0.4710 0.02595 0.01928 -0.0754 0.9303 1.0000
3.750 0.5121 0.02621 0.01981 -0.0780 0.9150 1.0000
4.000 0.5579 0.02621 0.02027 -0.0810 0.8973 1.0000
4.250 0.6978 0.01056 0.00143 -0.0795 0.0419 1.0000
4.500 0.7197 0.01337 0.00412 -0.0784 0.0387 1.0000
4.750 0.7558 0.01593 0.00672 -0.0791 0.0377 1.0000
5.000 0.7954 0.01900 0.00993 -0.0802 0.0378 1.0000
5.250 0.8308 0.02208 0.01325 -0.0805 0.0393 1.0000
5.500 0.8608 0.02447 0.01641 -0.0782 0.0462 1.0000
5.750 0.8892 0.02851 0.02111 -0.0759 0.0602 1.0000
9.750 0.9320 0.10802 0.10420 -0.0535 0.0760 1.0000
10.000 0.9113 0.11331 0.10956 -0.0565 0.0759 1.0000
10.250 0.8930 0.11984 0.11612 -0.0620 0.0757 1.0000
10.500 0.8768 0.12735 0.12358 -0.0700 0.0751 1.0000
10.750 0.8658 0.13374 0.12991 -0.0761 0.0728 1.0000
11.000 0.8635 0.13906 0.13521 -0.0794 0.0698 1.0000
11.250 0.8696 0.14336 0.13950 -0.0800 0.0665 1.0000
11.500 0.7508 0.14779 0.14425 -0.0728 0.0760 1.0000
11.750 0.7392 0.15153 0.14799 -0.0763 0.0755 1.0000
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Polar data table (+)
Polar graphs
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