EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 50,000 Max Cl/Cd: 29.77 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e817-il-50000-n5.txt Download as CSV file: xf-e817-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4950 0.10267 0.09580 -0.0510 1.0000 0.0298
-10.500 -0.5055 0.09759 0.09080 -0.0521 1.0000 0.0295
-10.250 -0.5199 0.09204 0.08533 -0.0535 1.0000 0.0292
-10.000 -0.5330 0.08738 0.08072 -0.0545 1.0000 0.0283
-9.750 -0.5520 0.08217 0.07554 -0.0559 1.0000 0.0279
-9.500 -0.5723 0.07750 0.07089 -0.0569 1.0000 0.0274
-9.250 -0.5944 0.07343 0.06682 -0.0573 1.0000 0.0270
-9.000 -0.6194 0.06993 0.06331 -0.0569 1.0000 0.0267
-8.750 -0.6448 0.06697 0.06032 -0.0558 1.0000 0.0264
-8.500 -0.6632 0.06346 0.05670 -0.0557 1.0000 0.0261
-8.250 -0.6766 0.05977 0.05279 -0.0554 1.0000 0.0261
-8.000 -0.6837 0.05597 0.04871 -0.0550 1.0000 0.0262
-7.750 -0.6843 0.05225 0.04464 -0.0547 1.0000 0.0265
-7.500 -0.6791 0.04868 0.04065 -0.0544 1.0000 0.0272
-7.250 -0.6688 0.04558 0.03711 -0.0539 1.0000 0.0288
-7.000 -0.6542 0.04290 0.03377 -0.0536 1.0000 0.0319
-6.750 -0.6403 0.04019 0.03104 -0.0530 1.0000 0.0349
-6.500 -0.6230 0.03804 0.02865 -0.0520 1.0000 0.0382
-6.250 -0.6045 0.03607 0.02636 -0.0506 1.0000 0.0416
-6.000 -0.5865 0.03398 0.02415 -0.0497 1.0000 0.0475
-5.750 -0.5665 0.03205 0.02213 -0.0499 1.0000 0.0618
-5.500 -0.5437 0.02975 0.01971 -0.0504 1.0000 0.0802
-5.250 -0.5168 0.02664 0.01720 -0.0533 1.0000 0.1450
-5.000 -0.4902 0.02531 0.01658 -0.0550 1.0000 0.2967
-4.750 -0.4667 0.02539 0.01657 -0.0546 1.0000 0.3575
-4.500 -0.4444 0.02566 0.01654 -0.0537 1.0000 0.4013
-4.250 -0.4234 0.02592 0.01669 -0.0523 1.0000 0.4326
-4.000 -0.4011 0.02593 0.01650 -0.0514 1.0000 0.4552
-3.750 -0.3780 0.02579 0.01614 -0.0508 1.0000 0.4714
-3.500 -0.3547 0.02563 0.01577 -0.0503 1.0000 0.4856
-3.250 -0.3310 0.02547 0.01541 -0.0499 1.0000 0.4992
-3.000 -0.3074 0.02533 0.01510 -0.0495 1.0000 0.5127
-2.750 -0.2838 0.02522 0.01483 -0.0491 1.0000 0.5263
-2.500 -0.2604 0.02515 0.01461 -0.0488 1.0000 0.5399
-2.250 -0.2369 0.02511 0.01436 -0.0484 1.0000 0.5539
-2.000 -0.2137 0.02510 0.01424 -0.0480 1.0000 0.5681
-1.750 -0.1874 0.02517 0.01421 -0.0482 0.9984 0.5830
-1.500 -0.1576 0.02537 0.01432 -0.0490 0.9952 0.5991
-1.250 -0.1279 0.02556 0.01443 -0.0499 0.9919 0.6159
-1.000 -0.0991 0.02574 0.01449 -0.0506 0.9882 0.6331
-0.750 -0.0703 0.02599 0.01473 -0.0512 0.9844 0.6500
-0.500 -0.0399 0.02631 0.01503 -0.0522 0.9810 0.6683
-0.250 -0.0132 0.02647 0.01519 -0.0525 0.9765 0.6871
0.000 0.0146 0.02672 0.01545 -0.0529 0.9720 0.7058
0.250 0.0448 0.02705 0.01580 -0.0538 0.9680 0.7270
0.500 0.0686 0.02718 0.01600 -0.0534 0.9625 0.7468
0.750 0.0969 0.02746 0.01635 -0.0538 0.9576 0.7697
1.000 0.1218 0.02764 0.01662 -0.0536 0.9521 0.7942
1.250 0.1466 0.02781 0.01691 -0.0533 0.9461 0.8210
1.500 0.1709 0.02795 0.01717 -0.0528 0.9402 0.8525
1.750 0.1960 0.02799 0.01736 -0.0526 0.9333 0.8958
2.000 0.2293 0.02795 0.01746 -0.0546 0.9252 1.0000
2.250 0.2678 0.02847 0.01802 -0.0579 0.9190 1.0000
2.500 0.3017 0.02893 0.01851 -0.0602 0.9117 1.0000
2.750 0.3395 0.02946 0.01909 -0.0630 0.9049 1.0000
3.000 0.3703 0.02989 0.01960 -0.0644 0.8959 1.0000
3.250 0.4070 0.03036 0.02018 -0.0668 0.8881 1.0000
3.500 0.4413 0.03077 0.02081 -0.0685 0.8787 1.0000
3.750 0.4724 0.03113 0.02134 -0.0697 0.8678 1.0000
4.000 0.5052 0.03145 0.02186 -0.0709 0.8566 1.0000
4.250 0.5393 0.03169 0.02233 -0.0722 0.8444 1.0000
4.500 0.5737 0.03178 0.02270 -0.0733 0.8307 1.0000
4.750 0.6106 0.03162 0.02297 -0.0744 0.8147 1.0000
5.000 0.6473 0.03106 0.02278 -0.0748 0.7941 1.0000
5.250 0.6833 0.02968 0.02180 -0.0738 0.7617 1.0000
5.500 0.7094 0.02799 0.02044 -0.0706 0.7121 1.0000
5.750 0.7399 0.02587 0.01858 -0.0670 0.6246 1.0000
6.000 0.7805 0.02622 0.01643 -0.0641 0.2294 1.0000
6.250 0.7866 0.02894 0.01817 -0.0616 0.1259 1.0000
6.500 0.8027 0.03119 0.02008 -0.0601 0.0873 1.0000
6.750 0.8245 0.03318 0.02194 -0.0594 0.0624 1.0000
7.000 0.8645 0.03562 0.02469 -0.0604 0.0489 1.0000
7.250 0.9061 0.03827 0.02742 -0.0624 0.0377 1.0000
7.500 0.9506 0.04137 0.03107 -0.0639 0.0326 1.0000
7.750 0.9838 0.04486 0.03498 -0.0643 0.0305 1.0000
8.000 1.0071 0.04835 0.03889 -0.0635 0.0293 1.0000
8.250 1.0227 0.05167 0.04255 -0.0621 0.0280 1.0000
8.500 1.0323 0.05549 0.04662 -0.0605 0.0267 1.0000
8.750 1.0360 0.05918 0.05073 -0.0578 0.0259 1.0000
9.000 1.0358 0.06251 0.05455 -0.0547 0.0254 1.0000
9.250 1.0311 0.06600 0.05846 -0.0515 0.0249 1.0000
9.500 1.0213 0.06937 0.06218 -0.0481 0.0246 1.0000
9.750 1.0086 0.07293 0.06602 -0.0450 0.0245 1.0000
10.000 0.9936 0.07670 0.07005 -0.0426 0.0244 1.0000
10.250 0.9772 0.08077 0.07434 -0.0410 0.0245 1.0000
10.500 0.9600 0.08522 0.07898 -0.0403 0.0246 1.0000
10.750 0.9422 0.09012 0.08405 -0.0406 0.0248 1.0000
11.000 0.9245 0.09554 0.08960 -0.0420 0.0251 1.0000
11.250 0.9080 0.10152 0.09567 -0.0445 0.0253 1.0000
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Polar data table (+)
Polar graphs
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