EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 50,000 Max Cl/Cd: 28.63 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e836-il-50000-n5.txt Download as CSV file: xf-e836-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6307 0.09779 0.09091 -0.0321 1.0000 0.0351
-11.750 -0.6480 0.09033 0.08342 -0.0368 1.0000 0.0346
-11.500 -0.6687 0.08352 0.07655 -0.0408 1.0000 0.0342
-11.250 -0.6889 0.07785 0.07079 -0.0435 1.0000 0.0338
-11.000 -0.7092 0.07288 0.06569 -0.0449 1.0000 0.0335
-10.750 -0.7283 0.06857 0.06121 -0.0452 1.0000 0.0333
-10.500 -0.7449 0.06483 0.05728 -0.0444 1.0000 0.0332
-10.250 -0.7601 0.06142 0.05366 -0.0427 1.0000 0.0332
-10.000 -0.7725 0.05834 0.05034 -0.0401 1.0000 0.0333
-9.750 -0.7814 0.05534 0.04707 -0.0372 1.0000 0.0335
-9.500 -0.7845 0.05226 0.04365 -0.0347 1.0000 0.0338
-9.250 -0.7830 0.04930 0.04031 -0.0322 1.0000 0.0348
-9.000 -0.7778 0.04658 0.03716 -0.0299 1.0000 0.0366
-8.750 -0.7694 0.04417 0.03426 -0.0275 1.0000 0.0388
-8.500 -0.7547 0.04158 0.03165 -0.0265 1.0000 0.0420
-8.250 -0.7330 0.03918 0.02899 -0.0256 1.0000 0.0449
-8.000 -0.7003 0.03670 0.02611 -0.0256 1.0000 0.0495
-7.750 -0.6814 0.03505 0.02449 -0.0245 1.0000 0.0569
-7.500 -0.6580 0.03341 0.02272 -0.0236 1.0000 0.0660
-7.250 -0.6416 0.03197 0.02103 -0.0215 1.0000 0.0749
-7.000 -0.6358 0.03066 0.01980 -0.0184 1.0000 0.0850
-6.750 -0.6340 0.02949 0.01876 -0.0147 1.0000 0.1032
-6.500 -0.6361 0.02829 0.01778 -0.0104 1.0000 0.1284
-6.250 -0.6421 0.02704 0.01687 -0.0055 1.0000 0.1637
-6.000 -0.6497 0.02578 0.01603 -0.0005 1.0000 0.2187
-5.750 -0.6588 0.02446 0.01529 0.0048 1.0000 0.2976
-5.500 -0.6658 0.02326 0.01488 0.0105 1.0000 0.4093
-5.250 -0.6559 0.02333 0.01573 0.0156 1.0000 0.5509
-5.000 -0.6474 0.02383 0.01626 0.0205 1.0000 0.6237
-4.750 -0.6370 0.02444 0.01673 0.0249 1.0000 0.6700
-4.500 -0.6267 0.02495 0.01703 0.0291 1.0000 0.7038
-4.250 -0.6130 0.02548 0.01735 0.0328 1.0000 0.7314
-4.000 -0.5821 0.02625 0.01774 0.0335 0.9962 0.7566
-3.750 -0.5493 0.02682 0.01801 0.0333 0.9913 0.7782
-3.500 -0.5124 0.02734 0.01824 0.0324 0.9871 0.7956
-3.250 -0.4747 0.02771 0.01832 0.0308 0.9830 0.8113
-3.000 -0.4390 0.02792 0.01828 0.0294 0.9784 0.8249
-2.750 -0.4025 0.02804 0.01812 0.0275 0.9738 0.8368
-2.500 -0.3651 0.02811 0.01796 0.0252 0.9694 0.8477
-2.250 -0.3360 0.02805 0.01773 0.0243 0.9636 0.8588
-2.000 -0.2921 0.02814 0.01763 0.0207 0.9598 0.8658
-1.750 -0.2550 0.02812 0.01743 0.0181 0.9553 0.8745
-1.500 -0.2205 0.02807 0.01726 0.0161 0.9499 0.8819
-1.250 -0.1848 0.02803 0.01712 0.0136 0.9448 0.8891
-1.000 -0.1408 0.02803 0.01699 0.0096 0.9411 0.8947
-0.750 -0.1132 0.02796 0.01687 0.0087 0.9345 0.9021
-0.500 -0.0706 0.02795 0.01681 0.0049 0.9301 0.9071
-0.250 -0.0409 0.02793 0.01675 0.0035 0.9241 0.9143
0.000 0.0000 0.02792 0.01674 0.0000 0.9188 0.9188
0.250 0.0409 0.02793 0.01676 -0.0035 0.9143 0.9241
0.500 0.0704 0.02795 0.01681 -0.0048 0.9071 0.9301
0.750 0.1133 0.02796 0.01687 -0.0087 0.9021 0.9345
1.000 0.1408 0.02803 0.01699 -0.0096 0.8947 0.9411
1.250 0.1849 0.02803 0.01712 -0.0137 0.8890 0.9448
1.500 0.2205 0.02807 0.01726 -0.0161 0.8819 0.9499
1.750 0.2551 0.02811 0.01742 -0.0181 0.8745 0.9554
2.000 0.2921 0.02813 0.01763 -0.0207 0.8658 0.9598
2.250 0.3361 0.02805 0.01773 -0.0243 0.8588 0.9636
2.500 0.3651 0.02811 0.01796 -0.0252 0.8478 0.9695
2.750 0.4026 0.02804 0.01811 -0.0275 0.8368 0.9738
3.000 0.4391 0.02791 0.01827 -0.0294 0.8249 0.9784
3.250 0.4748 0.02771 0.01832 -0.0308 0.8114 0.9830
3.500 0.5126 0.02733 0.01823 -0.0324 0.7956 0.9871
3.750 0.5495 0.02680 0.01799 -0.0334 0.7782 0.9913
4.000 0.5823 0.02625 0.01774 -0.0335 0.7567 0.9962
4.250 0.6129 0.02547 0.01734 -0.0328 0.7313 1.0000
4.500 0.6267 0.02494 0.01703 -0.0291 0.7038 1.0000
4.750 0.6370 0.02444 0.01672 -0.0250 0.6700 1.0000
5.000 0.6473 0.02383 0.01625 -0.0205 0.6235 1.0000
5.250 0.6559 0.02332 0.01573 -0.0156 0.5501 1.0000
5.500 0.6657 0.02325 0.01487 -0.0105 0.4088 1.0000
5.750 0.6589 0.02446 0.01529 -0.0048 0.2978 1.0000
6.000 0.6497 0.02578 0.01603 0.0005 0.2186 1.0000
6.250 0.6420 0.02704 0.01686 0.0055 0.1631 1.0000
6.500 0.6362 0.02829 0.01777 0.0104 0.1285 1.0000
6.750 0.6339 0.02949 0.01876 0.0147 0.1030 1.0000
7.000 0.6359 0.03066 0.01979 0.0184 0.0853 1.0000
7.250 0.6417 0.03197 0.02104 0.0215 0.0749 1.0000
7.500 0.6581 0.03341 0.02272 0.0236 0.0660 1.0000
7.750 0.6816 0.03506 0.02450 0.0245 0.0568 1.0000
8.000 0.7004 0.03671 0.02612 0.0256 0.0494 1.0000
8.250 0.7330 0.03916 0.02898 0.0256 0.0450 1.0000
8.500 0.7548 0.04158 0.03165 0.0265 0.0420 1.0000
8.750 0.7694 0.04415 0.03424 0.0275 0.0388 1.0000
9.000 0.7775 0.04655 0.03713 0.0299 0.0365 1.0000
9.250 0.7830 0.04927 0.04028 0.0323 0.0348 1.0000
9.500 0.7845 0.05225 0.04364 0.0347 0.0338 1.0000
9.750 0.7813 0.05536 0.04708 0.0373 0.0334 1.0000
10.000 0.7723 0.05836 0.05036 0.0401 0.0332 1.0000
10.250 0.7596 0.06148 0.05371 0.0427 0.0331 1.0000
10.500 0.7454 0.06479 0.05724 0.0444 0.0332 1.0000
10.750 0.7282 0.06862 0.06126 0.0452 0.0333 1.0000
11.000 0.7096 0.07287 0.06567 0.0449 0.0335 1.0000
11.250 0.6890 0.07788 0.07082 0.0434 0.0337 1.0000
11.500 0.6687 0.08361 0.07665 0.0407 0.0342 1.0000
11.750 0.6491 0.09021 0.08331 0.0368 0.0346 1.0000
12.000 0.6310 0.09787 0.09099 0.0320 0.0351 1.0000
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Polar data table (+)
Polar graphs
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