EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 200,000 Max Cl/Cd: 79.86 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e817-il-200000.txt Download as CSV file: xf-e817-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5902 0.08779 0.08461 -0.0506 1.0000 0.0439
-9.250 -0.6143 0.08449 0.08129 -0.0510 1.0000 0.0439
-9.000 -0.6418 0.08189 0.07868 -0.0502 1.0000 0.0439
-8.750 -0.6678 0.07934 0.07609 -0.0497 1.0000 0.0438
-8.500 -0.6863 0.07610 0.07273 -0.0499 1.0000 0.0439
-8.250 -0.7077 0.06646 0.06305 -0.0527 0.9991 0.0451
-8.000 -0.6971 0.06195 0.05857 -0.0538 0.9974 0.0462
-7.750 -0.6908 0.05759 0.05407 -0.0560 0.9954 0.0472
-7.500 -0.6834 0.04408 0.03943 -0.0590 0.9932 0.0184
-7.250 -0.6684 0.03900 0.03387 -0.0608 0.9910 0.0169
-7.000 -0.6481 0.03416 0.02842 -0.0619 0.9896 0.0155
-6.750 -0.6235 0.03051 0.02423 -0.0626 0.9885 0.0144
-6.500 -0.5964 0.02775 0.02108 -0.0632 0.9871 0.0140
-6.250 -0.5678 0.02566 0.01872 -0.0638 0.9856 0.0140
-6.000 -0.5385 0.02392 0.01680 -0.0647 0.9843 0.0149
-5.750 -0.5083 0.02250 0.01524 -0.0658 0.9832 0.0163
-5.500 -0.4752 0.02174 0.01435 -0.0674 0.9819 0.0209
-5.250 -0.4399 0.01961 0.01212 -0.0702 0.9808 0.0423
-5.000 -0.4057 0.01689 0.01068 -0.0742 0.9798 0.2826
-4.750 -0.3797 0.01685 0.01058 -0.0743 0.9778 0.3302
-4.500 -0.3519 0.01692 0.01056 -0.0747 0.9756 0.3572
-4.250 -0.3225 0.01706 0.01059 -0.0754 0.9735 0.3803
-4.000 -0.2921 0.01720 0.01068 -0.0763 0.9716 0.3993
-3.750 -0.2593 0.01745 0.01087 -0.0776 0.9698 0.4205
-3.500 -0.2292 0.01769 0.01106 -0.0784 0.9677 0.4413
-3.250 -0.2059 0.01767 0.01100 -0.0778 0.9646 0.4560
-3.000 -0.1781 0.01772 0.01098 -0.0782 0.9620 0.4687
-2.750 -0.1477 0.01782 0.01105 -0.0791 0.9596 0.4817
-2.500 -0.1142 0.01798 0.01118 -0.0805 0.9574 0.4956
-2.000 -0.0599 0.01816 0.01137 -0.0810 0.9513 0.5221
-1.750 -0.0313 0.01828 0.01146 -0.0815 0.9481 0.5363
-1.500 0.0018 0.01844 0.01163 -0.0828 0.9454 0.5512
-1.250 0.0375 0.01867 0.01190 -0.0847 0.9434 0.5662
-1.000 0.0587 0.01873 0.01200 -0.0837 0.9385 0.5798
-0.750 0.0877 0.01885 0.01218 -0.0843 0.9347 0.5942
-0.500 0.1223 0.01902 0.01240 -0.0858 0.9319 0.6100
-0.250 0.1607 0.01926 0.01269 -0.0881 0.9298 0.6261
0.000 0.1776 0.01930 0.01280 -0.0863 0.9229 0.6401
0.250 0.2121 0.01943 0.01300 -0.0878 0.9194 0.6569
0.500 0.2511 0.01959 0.01324 -0.0900 0.9170 0.6739
0.750 0.2697 0.01968 0.01342 -0.0885 0.9096 0.6888
1.000 0.3049 0.01975 0.01361 -0.0900 0.9060 0.7056
1.250 0.3452 0.01983 0.01380 -0.0924 0.9036 0.7238
1.500 0.3638 0.01991 0.01401 -0.0908 0.8951 0.7407
1.750 0.4029 0.01985 0.01409 -0.0928 0.8918 0.7586
2.000 0.4271 0.01987 0.01425 -0.0920 0.8840 0.7771
2.250 0.4646 0.01969 0.01422 -0.0936 0.8795 0.7968
2.500 0.5093 0.01937 0.01411 -0.0962 0.8769 0.8172
2.750 0.5306 0.01918 0.01408 -0.0946 0.8668 0.8387
3.000 0.5840 0.01828 0.01339 -0.0982 0.8638 0.8617
3.250 0.6119 0.01754 0.01284 -0.0970 0.8528 0.8886
3.500 0.6632 0.01567 0.01118 -0.0990 0.8418 0.9168
3.750 0.7187 0.01376 0.00956 -0.1019 0.8297 0.9550
4.000 0.7740 0.01214 0.00812 -0.1054 0.8121 1.0000
4.250 0.8025 0.01146 0.00754 -0.1046 0.7829 1.0000
4.500 0.8433 0.01056 0.00605 -0.1047 0.6160 1.0000
4.750 0.8348 0.01257 0.00666 -0.0979 0.3868 1.0000
5.000 0.8271 0.01488 0.00770 -0.0923 0.1746 1.0000
5.250 0.8321 0.01697 0.00892 -0.0889 0.0612 1.0000
5.500 0.8439 0.01875 0.01051 -0.0861 0.0275 1.0000
5.750 0.8607 0.02023 0.01208 -0.0839 0.0227 1.0000
6.000 0.8824 0.02173 0.01364 -0.0827 0.0203 1.0000
6.250 0.9114 0.02359 0.01565 -0.0828 0.0190 1.0000
6.500 0.9469 0.02597 0.01817 -0.0838 0.0186 1.0000
6.750 0.9848 0.02907 0.02157 -0.0848 0.0191 1.0000
7.000 1.0180 0.03330 0.02633 -0.0845 0.0208 1.0000
7.250 1.0404 0.03800 0.03154 -0.0827 0.0233 1.0000
7.500 1.0539 0.04270 0.03665 -0.0803 0.0249 1.0000
7.750 1.0617 0.04804 0.04234 -0.0776 0.0258 1.0000
11.750 0.8742 0.13356 0.13081 -0.0735 0.0349 1.0000
12.000 0.8707 0.14024 0.13746 -0.0776 0.0341 1.0000
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Polar data table (+)
Polar graphs
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