EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 100,000 Max Cl/Cd: 34.52 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e836-il-100000-n5.txt Download as CSV file: xf-e836-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6672 0.08671 0.08178 -0.0348 1.0000 0.0161
-12.000 -0.6887 0.07909 0.07406 -0.0398 1.0000 0.0159
-11.750 -0.7105 0.07274 0.06756 -0.0433 1.0000 0.0157
-11.500 -0.7318 0.06733 0.06199 -0.0452 1.0000 0.0156
-11.250 -0.7500 0.06290 0.05737 -0.0459 1.0000 0.0155
-11.000 -0.7675 0.05890 0.05316 -0.0456 1.0000 0.0155
-10.750 -0.7831 0.05533 0.04936 -0.0443 1.0000 0.0155
-10.500 -0.7956 0.05218 0.04597 -0.0423 1.0000 0.0154
-10.250 -0.8066 0.04923 0.04276 -0.0396 1.0000 0.0156
-10.000 -0.8143 0.04655 0.03979 -0.0365 1.0000 0.0157
-9.750 -0.8182 0.04393 0.03687 -0.0333 1.0000 0.0158
-9.500 -0.8161 0.04127 0.03386 -0.0306 1.0000 0.0161
-9.250 -0.8096 0.03893 0.03114 -0.0282 1.0000 0.0168
-9.000 -0.8002 0.03714 0.02897 -0.0259 1.0000 0.0180
-8.750 -0.7881 0.03465 0.02625 -0.0242 1.0000 0.0191
-8.500 -0.7757 0.03281 0.02433 -0.0225 1.0000 0.0204
-8.250 -0.7610 0.03114 0.02252 -0.0207 1.0000 0.0214
-8.000 -0.7476 0.02962 0.02088 -0.0185 1.0000 0.0228
-7.750 -0.7373 0.02834 0.01948 -0.0158 1.0000 0.0241
-7.500 -0.7320 0.02732 0.01835 -0.0122 1.0000 0.0255
-7.250 -0.7309 0.02649 0.01743 -0.0080 1.0000 0.0275
-7.000 -0.7136 0.02523 0.01616 -0.0073 0.9946 0.0327
-6.750 -0.6877 0.02402 0.01466 -0.0078 0.9871 0.0385
-6.500 -0.6623 0.02277 0.01339 -0.0085 0.9805 0.0497
-6.250 -0.6394 0.02146 0.01214 -0.0086 0.9729 0.0657
-6.000 -0.6148 0.02021 0.01108 -0.0090 0.9669 0.1044
-5.750 -0.5945 0.01893 0.01029 -0.0089 0.9596 0.1852
-5.500 -0.5763 0.01752 0.00956 -0.0086 0.9533 0.3085
-5.250 -0.5642 0.01633 0.00918 -0.0064 0.9452 0.4498
-5.000 -0.5386 0.01603 0.00938 -0.0055 0.9410 0.5676
-4.750 -0.5155 0.01616 0.00953 -0.0041 0.9342 0.6227
-4.500 -0.4859 0.01638 0.00960 -0.0039 0.9297 0.6598
-4.250 -0.4579 0.01658 0.00967 -0.0036 0.9248 0.6850
-4.000 -0.4331 0.01674 0.00967 -0.0028 0.9189 0.7056
-3.750 -0.4020 0.01698 0.00976 -0.0030 0.9151 0.7223
-3.500 -0.3758 0.01717 0.00983 -0.0024 0.9097 0.7362
-3.250 -0.3493 0.01731 0.00980 -0.0020 0.9045 0.7489
-3.000 -0.3178 0.01747 0.00983 -0.0024 0.9009 0.7598
-2.750 -0.2906 0.01765 0.00993 -0.0020 0.8956 0.7687
-2.500 -0.2648 0.01771 0.00988 -0.0016 0.8905 0.7782
-2.250 -0.2341 0.01776 0.00984 -0.0021 0.8869 0.7863
-2.000 -0.2097 0.01784 0.00983 -0.0014 0.8811 0.7935
-1.750 -0.1848 0.01783 0.00974 -0.0010 0.8760 0.8018
-1.500 -0.1525 0.01786 0.00971 -0.0017 0.8727 0.8071
-1.250 -0.1314 0.01789 0.00969 -0.0007 0.8662 0.8142
-1.000 -0.1040 0.01788 0.00963 -0.0007 0.8616 0.8198
-0.750 -0.0731 0.01787 0.00958 -0.0013 0.8581 0.8246
-0.500 -0.0554 0.01786 0.00956 0.0002 0.8510 0.8319
-0.250 -0.0240 0.01787 0.00955 -0.0005 0.8469 0.8357
0.000 0.0000 0.01787 0.00954 0.0000 0.8416 0.8416
0.250 0.0240 0.01787 0.00955 0.0005 0.8357 0.8470
0.500 0.0553 0.01786 0.00956 -0.0002 0.8319 0.8510
0.750 0.0730 0.01787 0.00958 0.0014 0.8245 0.8582
1.000 0.1040 0.01787 0.00963 0.0007 0.8198 0.8616
1.250 0.1314 0.01789 0.00969 0.0007 0.8141 0.8662
1.500 0.1525 0.01786 0.00971 0.0018 0.8071 0.8727
1.750 0.1848 0.01783 0.00974 0.0010 0.8017 0.8760
2.250 0.2341 0.01776 0.00984 0.0021 0.7863 0.8869
2.500 0.2648 0.01770 0.00988 0.0016 0.7782 0.8905
2.750 0.2906 0.01765 0.00993 0.0020 0.7687 0.8956
3.000 0.3178 0.01746 0.00983 0.0024 0.7598 0.9009
3.250 0.3493 0.01731 0.00980 0.0020 0.7489 0.9044
3.500 0.3758 0.01717 0.00983 0.0024 0.7362 0.9096
3.750 0.4020 0.01697 0.00976 0.0030 0.7223 0.9151
4.000 0.4333 0.01674 0.00967 0.0028 0.7057 0.9189
4.250 0.4580 0.01658 0.00966 0.0036 0.6848 0.9248
4.500 0.4860 0.01638 0.00960 0.0039 0.6598 0.9297
4.750 0.5156 0.01616 0.00953 0.0041 0.6229 0.9342
5.000 0.5387 0.01603 0.00938 0.0055 0.5676 0.9409
5.250 0.5641 0.01634 0.00918 0.0064 0.4483 0.9452
5.500 0.5765 0.01751 0.00956 0.0085 0.3088 0.9532
5.750 0.5947 0.01893 0.01029 0.0089 0.1854 0.9596
6.000 0.6150 0.02021 0.01108 0.0090 0.1044 0.9668
6.250 0.6394 0.02147 0.01214 0.0086 0.0653 0.9729
6.500 0.6623 0.02277 0.01339 0.0085 0.0497 0.9804
6.750 0.6877 0.02402 0.01467 0.0078 0.0384 0.9871
7.000 0.7136 0.02523 0.01616 0.0073 0.0329 0.9946
7.250 0.7311 0.02649 0.01744 0.0079 0.0276 1.0000
7.500 0.7320 0.02733 0.01836 0.0122 0.0255 1.0000
7.750 0.7374 0.02836 0.01950 0.0158 0.0241 1.0000
8.000 0.7476 0.02964 0.02089 0.0185 0.0227 1.0000
8.250 0.7612 0.03115 0.02253 0.0207 0.0215 1.0000
8.500 0.7759 0.03283 0.02435 0.0225 0.0205 1.0000
8.750 0.7883 0.03464 0.02625 0.0242 0.0192 1.0000
9.000 0.7998 0.03705 0.02889 0.0260 0.0179 1.0000
9.250 0.8095 0.03890 0.03110 0.0282 0.0168 1.0000
9.500 0.8160 0.04126 0.03386 0.0306 0.0161 1.0000
9.750 0.8180 0.04392 0.03686 0.0333 0.0158 1.0000
10.000 0.8141 0.04653 0.03978 0.0365 0.0156 1.0000
10.250 0.8060 0.04927 0.04280 0.0397 0.0155 1.0000
10.500 0.7963 0.05209 0.04588 0.0423 0.0155 1.0000
10.750 0.7827 0.05538 0.04942 0.0443 0.0155 1.0000
11.000 0.7678 0.05886 0.05313 0.0456 0.0155 1.0000
11.250 0.7502 0.06289 0.05736 0.0459 0.0155 1.0000
11.500 0.7314 0.06742 0.06209 0.0452 0.0156 1.0000
11.750 0.7117 0.07259 0.06741 0.0433 0.0157 1.0000
12.000 0.6890 0.07912 0.07408 0.0398 0.0159 1.0000
12.250 0.6678 0.08668 0.08175 0.0348 0.0161 1.0000
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Polar data table (+)
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