EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 50,000 Max Cl/Cd: 26.86 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e817-il-50000.txt Download as CSV file: xf-e817-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5775 0.08814 0.08203 -0.0506 1.0000 0.0946
-8.750 -0.5884 0.08449 0.07846 -0.0495 1.0000 0.0938
-8.500 -0.5999 0.08102 0.07506 -0.0482 1.0000 0.0916
-8.250 -0.6683 0.07329 0.06707 -0.0546 1.0000 0.0817
-8.000 -0.6693 0.06899 0.06277 -0.0538 1.0000 0.0803
-7.750 -0.6764 0.06442 0.05804 -0.0540 1.0000 0.0790
-7.500 -0.6812 0.05947 0.05281 -0.0548 1.0000 0.0779
-7.250 -0.6793 0.05461 0.04752 -0.0557 1.0000 0.0770
-7.000 -0.6713 0.04993 0.04225 -0.0568 1.0000 0.0791
-6.750 -0.6561 0.04577 0.03737 -0.0578 1.0000 0.0810
-6.500 -0.6373 0.04173 0.03293 -0.0582 1.0000 0.0845
-6.250 -0.6151 0.03851 0.02942 -0.0578 1.0000 0.0882
-6.000 -0.5898 0.03547 0.02579 -0.0572 1.0000 0.0942
-5.750 -0.5679 0.03277 0.02318 -0.0565 1.0000 0.1117
-5.500 -0.5448 0.03014 0.02069 -0.0555 1.0000 0.1384
-5.250 -0.5187 0.02741 0.01873 -0.0563 1.0000 0.2199
-5.000 -0.5019 0.02831 0.02074 -0.0523 1.0000 0.3964
-4.750 -0.4911 0.02996 0.02244 -0.0465 1.0000 0.4478
-4.500 -0.4799 0.03118 0.02361 -0.0410 1.0000 0.4858
-4.250 -0.4701 0.03215 0.02441 -0.0353 1.0000 0.5150
-4.000 -0.4577 0.03261 0.02476 -0.0307 1.0000 0.5418
-3.750 -0.4405 0.03247 0.02443 -0.0282 1.0000 0.5661
-3.500 -0.4243 0.03224 0.02404 -0.0253 1.0000 0.5843
-3.250 -0.4017 0.03159 0.02315 -0.0250 1.0000 0.6037
-3.000 -0.3797 0.03098 0.02232 -0.0244 1.0000 0.6202
-2.750 -0.3591 0.03044 0.02162 -0.0234 1.0000 0.6357
-2.500 -0.3375 0.02990 0.02091 -0.0228 1.0000 0.6513
-2.250 -0.3152 0.02939 0.02023 -0.0224 1.0000 0.6678
-2.000 -0.2905 0.02886 0.01943 -0.0228 1.0000 0.6862
-1.750 -0.2715 0.02846 0.01894 -0.0215 1.0000 0.7023
-1.500 -0.2522 0.02808 0.01847 -0.0203 1.0000 0.7197
-1.250 -0.2296 0.02771 0.01798 -0.0201 1.0000 0.7399
-1.000 -0.2121 0.02738 0.01760 -0.0184 1.0000 0.7585
-0.750 -0.1914 0.02708 0.01721 -0.0178 1.0000 0.7809
-0.500 -0.1757 0.02675 0.01680 -0.0157 1.0000 0.8023
-0.250 -0.1594 0.02642 0.01645 -0.0140 1.0000 0.8269
0.000 -0.1446 0.02606 0.01608 -0.0119 1.0000 0.8546
0.250 -0.1304 0.02564 0.01567 -0.0098 1.0000 0.8876
0.500 -0.1124 0.02511 0.01521 -0.0085 1.0000 0.9303
0.750 -0.0765 0.02438 0.01451 -0.0123 1.0000 1.0000
1.000 -0.0353 0.02461 0.01458 -0.0185 1.0000 1.0000
1.250 0.0052 0.02504 0.01487 -0.0240 1.0000 1.0000
1.500 0.0423 0.02557 0.01528 -0.0283 1.0000 1.0000
1.750 0.0756 0.02616 0.01577 -0.0316 1.0000 1.0000
2.000 0.1055 0.02678 0.01631 -0.0340 1.0000 1.0000
2.250 0.1330 0.02744 0.01691 -0.0358 1.0000 1.0000
2.500 0.1587 0.02814 0.01758 -0.0371 1.0000 1.0000
2.750 0.1829 0.02888 0.01831 -0.0381 1.0000 1.0000
3.000 0.2061 0.02966 0.01917 -0.0390 1.0000 1.0000
3.250 0.2282 0.03050 0.02004 -0.0397 1.0000 1.0000
3.500 0.2495 0.03140 0.02100 -0.0403 1.0000 1.0000
3.750 0.2699 0.03236 0.02204 -0.0408 1.0000 1.0000
4.000 0.2896 0.03339 0.02316 -0.0414 1.0000 1.0000
4.250 0.3085 0.03450 0.02438 -0.0418 1.0000 1.0000
4.500 0.3265 0.03569 0.02577 -0.0423 1.0000 1.0000
4.750 0.3438 0.03698 0.02720 -0.0428 1.0000 1.0000
5.000 0.4022 0.03967 0.03022 -0.0510 0.9737 1.0000
5.250 0.4689 0.04178 0.03275 -0.0593 0.9352 1.0000
5.500 0.5306 0.04302 0.03457 -0.0657 0.8969 1.0000
5.750 0.6133 0.04275 0.03499 -0.0726 0.8484 1.0000
6.000 0.7573 0.03230 0.02603 -0.0745 0.7385 1.0000
6.250 0.8037 0.02992 0.01977 -0.0611 0.1740 1.0000
6.500 0.9105 0.03636 0.02561 -0.0711 0.1006 1.0000
6.750 0.9455 0.03959 0.02914 -0.0715 0.0857 1.0000
7.000 0.9776 0.04316 0.03323 -0.0710 0.0806 1.0000
7.250 1.0039 0.04718 0.03779 -0.0698 0.0803 1.0000
7.500 1.0227 0.05140 0.04259 -0.0676 0.0820 1.0000
7.750 1.0364 0.05580 0.04748 -0.0653 0.0846 1.0000
8.000 1.0502 0.06065 0.05263 -0.0635 0.0870 1.0000
8.250 1.0465 0.06443 0.05725 -0.0591 0.0931 1.0000
8.500 1.0466 0.06934 0.06254 -0.0564 0.0979 1.0000
8.750 1.0367 0.07404 0.06777 -0.0530 0.1066 1.0000
9.000 1.0285 0.07939 0.07348 -0.0507 0.1175 1.0000
9.250 1.0250 0.08742 0.08176 -0.0502 0.1399 1.0000
9.500 0.9744 0.09009 0.08473 -0.0468 0.1439 1.0000
9.750 0.9374 0.09540 0.09014 -0.0471 0.1476 1.0000
10.000 0.9045 0.10427 0.09911 -0.0522 0.1700 1.0000
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Polar data table (+)
Polar graphs
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