EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 100,000 Max Cl/Cd: 40.89 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e817-il-100000.txt Download as CSV file: xf-e817-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 817 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5172 0.11352 0.10903 -0.0413 1.0000 0.1213
-9.750 -0.5481 0.08797 0.08345 -0.0519 1.0000 0.0430
-9.500 -0.5566 0.08451 0.08006 -0.0506 1.0000 0.0417
-9.250 -0.5721 0.08034 0.07593 -0.0506 1.0000 0.0401
-9.000 -0.5977 0.07554 0.07115 -0.0517 1.0000 0.0394
-8.750 -0.6258 0.07171 0.06733 -0.0518 1.0000 0.0387
-8.500 -0.6541 0.06906 0.06467 -0.0508 1.0000 0.0388
-8.250 -0.6766 0.06503 0.06052 -0.0519 1.0000 0.0384
-8.000 -0.6932 0.06037 0.05563 -0.0525 1.0000 0.0371
-7.750 -0.7109 0.05352 0.04797 -0.0544 1.0000 0.0335
-7.500 -0.6986 0.05154 0.04554 -0.0536 1.0000 0.0318
-7.250 -0.6909 0.04631 0.04002 -0.0541 1.0000 0.0309
-7.000 -0.6760 0.04356 0.03664 -0.0545 1.0000 0.0321
-6.750 -0.6586 0.03926 0.03185 -0.0551 1.0000 0.0324
-6.500 -0.6399 0.03522 0.02759 -0.0559 1.0000 0.0353
-6.250 -0.6173 0.03281 0.02488 -0.0558 1.0000 0.0372
-6.000 -0.5928 0.03029 0.02204 -0.0554 1.0000 0.0388
-5.750 -0.5683 0.02822 0.01973 -0.0546 1.0000 0.0413
-5.500 -0.5442 0.02593 0.01739 -0.0539 1.0000 0.0463
-5.250 -0.5187 0.02417 0.01572 -0.0545 1.0000 0.0641
-5.000 -0.4779 0.01959 0.01262 -0.0599 1.0000 0.2801
-4.750 -0.4535 0.01999 0.01301 -0.0595 1.0000 0.3693
-4.500 -0.4308 0.02038 0.01315 -0.0587 1.0000 0.4050
-4.250 -0.4082 0.02064 0.01329 -0.0578 1.0000 0.4310
-4.000 -0.3865 0.02090 0.01350 -0.0567 1.0000 0.4545
-3.750 -0.3654 0.02115 0.01374 -0.0553 1.0000 0.4758
-3.500 -0.3425 0.02129 0.01377 -0.0546 1.0000 0.4964
-3.250 -0.3195 0.02130 0.01369 -0.0539 1.0000 0.5117
-3.000 -0.2959 0.02126 0.01355 -0.0535 1.0000 0.5254
-2.750 -0.2722 0.02122 0.01342 -0.0531 1.0000 0.5388
-2.500 -0.2486 0.02120 0.01327 -0.0527 1.0000 0.5523
-2.250 -0.2253 0.02121 0.01322 -0.0523 1.0000 0.5660
-2.000 -0.2023 0.02124 0.01322 -0.0518 1.0000 0.5800
-1.750 -0.1795 0.02130 0.01325 -0.0513 1.0000 0.5943
-1.500 -0.1570 0.02138 0.01333 -0.0507 1.0000 0.6090
-1.250 -0.1346 0.02149 0.01344 -0.0502 1.0000 0.6242
-1.000 -0.1125 0.02162 0.01353 -0.0496 1.0000 0.6400
-0.750 -0.0904 0.02178 0.01369 -0.0490 1.0000 0.6568
-0.500 -0.0686 0.02196 0.01389 -0.0484 1.0000 0.6739
-0.250 -0.0481 0.02216 0.01414 -0.0475 1.0000 0.6904
0.000 -0.0275 0.02238 0.01441 -0.0467 1.0000 0.7084
0.250 -0.0067 0.02262 0.01468 -0.0460 1.0000 0.7279
0.500 0.0123 0.02287 0.01501 -0.0448 1.0000 0.7468
0.750 0.0319 0.02315 0.01535 -0.0439 1.0000 0.7683
1.000 0.0500 0.02343 0.01572 -0.0426 1.0000 0.7903
1.250 0.0674 0.02372 0.01611 -0.0412 1.0000 0.8147
1.500 0.1015 0.02446 0.01695 -0.0430 0.9917 0.8452
1.750 0.1365 0.02518 0.01781 -0.0446 0.9817 0.8835
2.000 0.1713 0.02527 0.01810 -0.0466 0.9700 0.9539
2.250 0.2182 0.02578 0.01860 -0.0522 0.9581 1.0000
2.500 0.2634 0.02643 0.01928 -0.0570 0.9469 1.0000
2.750 0.3063 0.02706 0.01993 -0.0610 0.9357 1.0000
3.000 0.3485 0.02767 0.02057 -0.0646 0.9246 1.0000
3.250 0.3917 0.02823 0.02121 -0.0681 0.9137 1.0000
3.500 0.4397 0.02874 0.02188 -0.0722 0.9035 1.0000
3.750 0.4813 0.02898 0.02226 -0.0750 0.8905 1.0000
4.000 0.5272 0.02903 0.02248 -0.0781 0.8770 1.0000
4.250 0.5636 0.02883 0.02247 -0.0793 0.8592 1.0000
4.500 0.6245 0.02764 0.02166 -0.0832 0.8403 1.0000
4.750 0.6979 0.02471 0.01913 -0.0869 0.8142 1.0000
5.000 0.7635 0.02095 0.01582 -0.0882 0.7825 1.0000
5.250 0.7855 0.01921 0.01434 -0.0841 0.7371 1.0000
5.500 0.8219 0.02077 0.01196 -0.0801 0.1279 1.0000
5.750 0.8316 0.02315 0.01393 -0.0769 0.0792 1.0000
6.000 0.8517 0.02537 0.01599 -0.0755 0.0552 1.0000
6.250 0.8889 0.02824 0.01880 -0.0766 0.0445 1.0000
6.500 0.9270 0.03143 0.02207 -0.0784 0.0371 1.0000
6.750 0.9634 0.03443 0.02544 -0.0789 0.0359 1.0000
7.000 0.9936 0.03796 0.02939 -0.0785 0.0359 1.0000
7.250 1.0174 0.04199 0.03384 -0.0774 0.0366 1.0000
7.500 1.0394 0.04701 0.03917 -0.0765 0.0380 1.0000
7.750 1.0500 0.05003 0.04323 -0.0713 0.0444 1.0000
8.000 1.0621 0.05627 0.04967 -0.0697 0.0490 1.0000
11.000 0.8151 0.12224 0.11890 -0.0492 0.1142 1.0000
11.250 0.7702 0.13077 0.12742 -0.0581 0.1139 1.0000
11.500 0.7240 0.13738 0.13396 -0.0671 0.1090 1.0000
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Polar data table (+)
Polar graphs
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