EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 100,000 Max Cl/Cd: 43.1 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e836-il-100000.txt Download as CSV file: xf-e836-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E836 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6579 0.06203 0.05724 -0.0477 1.0000 0.0604
-10.250 -0.6763 0.05749 0.05260 -0.0471 1.0000 0.0592
-10.000 -0.6974 0.05330 0.04829 -0.0455 1.0000 0.0577
-9.750 -0.7809 0.06073 0.05527 -0.0387 1.0000 0.0586
-9.500 -0.8009 0.05596 0.05014 -0.0350 1.0000 0.0541
-9.250 -0.8126 0.05250 0.04607 -0.0304 1.0000 0.0489
-9.000 -0.8130 0.04885 0.04218 -0.0276 1.0000 0.0481
-8.750 -0.8139 0.04607 0.03906 -0.0242 1.0000 0.0484
-8.500 -0.8134 0.04343 0.03609 -0.0205 1.0000 0.0486
-8.250 -0.8113 0.04092 0.03328 -0.0167 1.0000 0.0486
-8.000 -0.8089 0.03867 0.03071 -0.0128 1.0000 0.0488
-7.750 -0.8039 0.03630 0.02803 -0.0090 1.0000 0.0487
-7.500 -0.7953 0.03415 0.02556 -0.0057 1.0000 0.0489
-7.250 -0.7836 0.03228 0.02337 -0.0027 1.0000 0.0497
-7.000 -0.7634 0.02973 0.02064 -0.0012 1.0000 0.0512
-6.750 -0.7485 0.02805 0.01899 0.0005 1.0000 0.0563
-6.500 -0.7339 0.02691 0.01766 0.0030 1.0000 0.0618
-6.250 -0.7184 0.02507 0.01596 0.0051 1.0000 0.0673
-6.000 -0.7085 0.02406 0.01491 0.0080 1.0000 0.0766
-5.750 -0.7018 0.02290 0.01382 0.0114 1.0000 0.0892
-5.500 -0.6982 0.02155 0.01268 0.0152 1.0000 0.1103
-5.250 -0.7025 0.01932 0.01131 0.0201 1.0000 0.1994
-5.000 -0.7125 0.01695 0.01043 0.0258 1.0000 0.4176
-4.750 -0.7095 0.01648 0.01093 0.0313 1.0000 0.6007
-4.500 -0.6987 0.01705 0.01162 0.0359 1.0000 0.6799
-4.250 -0.6877 0.01793 0.01241 0.0406 1.0000 0.7286
-4.000 -0.6746 0.01876 0.01315 0.0449 1.0000 0.7597
-3.750 -0.6594 0.01958 0.01385 0.0488 1.0000 0.7835
-3.500 -0.6441 0.02025 0.01440 0.0525 1.0000 0.8046
-3.250 -0.6150 0.02115 0.01514 0.0536 0.9967 0.8246
-3.000 -0.5833 0.02186 0.01563 0.0536 0.9923 0.8437
-2.750 -0.5430 0.02272 0.01630 0.0523 0.9884 0.8591
-2.500 -0.4966 0.02351 0.01689 0.0494 0.9850 0.8729
-2.250 -0.4495 0.02414 0.01730 0.0459 0.9817 0.8856
-2.000 -0.3788 0.02493 0.01789 0.0380 0.9802 0.8924
-1.750 -0.3322 0.02514 0.01797 0.0337 0.9763 0.9017
-1.500 -0.2712 0.02545 0.01811 0.0267 0.9735 0.9078
-1.250 -0.2228 0.02562 0.01818 0.0217 0.9699 0.9156
-1.000 -0.1755 0.02567 0.01814 0.0170 0.9657 0.9218
-0.750 -0.1371 0.02569 0.01810 0.0138 0.9603 0.9293
-0.500 -0.0806 0.02577 0.01813 0.0073 0.9570 0.9340
-0.250 -0.0537 0.02577 0.01811 0.0061 0.9503 0.9419
0.000 -0.0001 0.02574 0.01807 0.0000 0.9459 0.9459
0.250 0.0532 0.02577 0.01811 -0.0061 0.9420 0.9504
0.500 0.0806 0.02577 0.01813 -0.0073 0.9340 0.9570
0.750 0.1371 0.02569 0.01810 -0.0139 0.9294 0.9603
1.000 0.1753 0.02568 0.01814 -0.0170 0.9219 0.9657
1.250 0.2230 0.02562 0.01817 -0.0218 0.9156 0.9699
1.500 0.2712 0.02545 0.01811 -0.0267 0.9078 0.9735
1.750 0.3322 0.02514 0.01797 -0.0337 0.9017 0.9763
2.000 0.3789 0.02493 0.01789 -0.0380 0.8923 0.9802
2.250 0.4494 0.02415 0.01731 -0.0459 0.8856 0.9817
2.500 0.4970 0.02350 0.01689 -0.0495 0.8729 0.9850
2.750 0.5429 0.02273 0.01631 -0.0524 0.8591 0.9884
3.000 0.5835 0.02185 0.01562 -0.0537 0.8437 0.9922
3.250 0.6150 0.02114 0.01513 -0.0536 0.8244 0.9967
3.500 0.6444 0.02023 0.01439 -0.0525 0.8045 1.0000
3.750 0.6596 0.01957 0.01385 -0.0488 0.7833 1.0000
4.000 0.6749 0.01876 0.01315 -0.0449 0.7597 1.0000
4.250 0.6877 0.01792 0.01240 -0.0406 0.7279 1.0000
4.500 0.6990 0.01704 0.01160 -0.0359 0.6792 1.0000
4.750 0.7098 0.01647 0.01092 -0.0314 0.5999 1.0000
5.000 0.7126 0.01697 0.01043 -0.0258 0.4150 1.0000
5.250 0.7027 0.01933 0.01131 -0.0201 0.1991 1.0000
5.500 0.6984 0.02155 0.01268 -0.0153 0.1101 1.0000
5.750 0.7012 0.02299 0.01389 -0.0113 0.0885 1.0000
6.000 0.7086 0.02409 0.01493 -0.0081 0.0765 1.0000
6.250 0.7185 0.02509 0.01597 -0.0051 0.0671 1.0000
6.500 0.7341 0.02691 0.01767 -0.0030 0.0615 1.0000
6.750 0.7490 0.02806 0.01900 -0.0006 0.0565 1.0000
7.000 0.7653 0.03003 0.02092 0.0009 0.0508 1.0000
7.250 0.7837 0.03227 0.02337 0.0027 0.0496 1.0000
7.500 0.7957 0.03418 0.02560 0.0057 0.0489 1.0000
7.750 0.8039 0.03633 0.02807 0.0090 0.0486 1.0000
8.000 0.8093 0.03870 0.03074 0.0127 0.0488 1.0000
8.250 0.8121 0.04106 0.03341 0.0166 0.0489 1.0000
8.500 0.8138 0.04349 0.03615 0.0204 0.0488 1.0000
8.750 0.8140 0.04602 0.03902 0.0242 0.0484 1.0000
9.000 0.8127 0.04879 0.04213 0.0277 0.0480 1.0000
9.250 0.8130 0.05245 0.04602 0.0303 0.0490 1.0000
9.500 0.8007 0.05597 0.05015 0.0351 0.0539 1.0000
9.750 0.7807 0.06075 0.05529 0.0387 0.0587 1.0000
10.000 0.6973 0.05322 0.04820 0.0456 0.0580 1.0000
10.250 0.6741 0.05722 0.05234 0.0473 0.0587 1.0000
10.500 0.6557 0.06191 0.05713 0.0478 0.0603 1.0000
10.750 0.5875 0.10096 0.09624 0.0228 0.1475 1.0000
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Polar data table (+)
Polar graphs
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