EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Reynolds number: 100,000 Max Cl/Cd: 41.19 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e874-il-100000.txt Download as CSV file: xf-e874-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 874 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5681 0.10849 0.10360 0.0007 1.0000 0.1039
-9.250 -0.5688 0.10493 0.10007 -0.0011 1.0000 0.1085
-9.000 -0.5988 0.10213 0.09745 -0.0097 1.0000 0.1116
-8.750 -0.5773 0.09672 0.09201 -0.0056 1.0000 0.1142
-8.500 -0.5693 0.09324 0.08854 -0.0051 1.0000 0.1174
-7.750 -0.5914 0.08114 0.07667 -0.0124 1.0000 0.1280
-7.500 -0.5874 0.07734 0.07289 -0.0128 1.0000 0.1307
-6.750 -0.6171 0.05090 0.04536 -0.0266 1.0000 0.0742
-6.500 -0.6062 0.04381 0.03798 -0.0252 1.0000 0.0558
-6.250 -0.5978 0.03824 0.03146 -0.0227 1.0000 0.0471
-6.000 -0.5851 0.03397 0.02683 -0.0208 1.0000 0.0447
-5.750 -0.5692 0.03036 0.02268 -0.0187 1.0000 0.0423
-5.500 -0.5501 0.02726 0.01898 -0.0166 1.0000 0.0406
-5.250 -0.5281 0.02471 0.01602 -0.0148 1.0000 0.0400
-5.000 -0.5053 0.02260 0.01366 -0.0132 1.0000 0.0405
-4.750 -0.4830 0.02081 0.01174 -0.0116 1.0000 0.0425
-4.500 -0.4615 0.01935 0.01015 -0.0099 1.0000 0.0462
-4.250 -0.4421 0.01787 0.00866 -0.0081 1.0000 0.0567
-4.000 -0.4260 0.01546 0.00705 -0.0055 1.0000 0.1561
-3.750 -0.4074 0.01512 0.00695 -0.0040 1.0000 0.2901
-3.500 -0.3875 0.01478 0.00667 -0.0025 1.0000 0.3414
-3.250 -0.3656 0.01412 0.00612 -0.0012 1.0000 0.3827
-3.000 -0.3444 0.01336 0.00561 0.0003 1.0000 0.4370
-2.750 -0.3242 0.01251 0.00520 0.0020 1.0000 0.5240
-2.500 -0.3021 0.01154 0.00494 0.0040 1.0000 0.6803
-2.250 -0.1568 0.01151 0.00495 -0.0175 1.0000 0.9840
-2.000 -0.1123 0.01139 0.00453 -0.0215 1.0000 1.0000
-1.750 -0.0951 0.01127 0.00422 -0.0199 1.0000 1.0000
-1.500 -0.0770 0.01120 0.00402 -0.0183 1.0000 1.0000
-1.250 -0.0587 0.01116 0.00388 -0.0167 1.0000 1.0000
-1.000 -0.0404 0.01115 0.00378 -0.0151 1.0000 1.0000
-0.750 -0.0224 0.01118 0.00375 -0.0135 1.0000 1.0000
-0.500 -0.0051 0.01123 0.00375 -0.0118 1.0000 1.0000
-0.250 0.0107 0.01135 0.00384 -0.0099 1.0000 1.0000
0.000 0.0233 0.01155 0.00404 -0.0077 1.0000 1.0000
0.250 0.0297 0.01195 0.00444 -0.0049 1.0000 1.0000
0.500 0.1011 0.01208 0.00462 -0.0146 0.9774 1.0000
0.750 0.1663 0.01201 0.00463 -0.0226 0.9509 1.0000
1.000 0.2326 0.01179 0.00450 -0.0304 0.9231 1.0000
1.250 0.2952 0.01156 0.00434 -0.0371 0.8883 1.0000
1.500 0.3424 0.01154 0.00434 -0.0405 0.8468 1.0000
1.750 0.3757 0.01174 0.00447 -0.0410 0.8093 1.0000
2.000 0.4027 0.01203 0.00471 -0.0405 0.7774 1.0000
2.250 0.4279 0.01236 0.00501 -0.0396 0.7507 1.0000
2.500 0.4524 0.01272 0.00542 -0.0386 0.7276 1.0000
2.750 0.4763 0.01308 0.00584 -0.0377 0.7064 1.0000
3.000 0.5002 0.01345 0.00627 -0.0366 0.6874 1.0000
3.250 0.5239 0.01383 0.00675 -0.0355 0.6688 1.0000
3.500 0.5467 0.01416 0.00721 -0.0341 0.6476 1.0000
3.750 0.5631 0.01412 0.00714 -0.0304 0.5991 1.0000
4.000 0.5729 0.01391 0.00662 -0.0252 0.5055 1.0000
4.250 0.5663 0.01692 0.00727 -0.0187 0.0830 1.0000
4.500 0.5821 0.01860 0.00885 -0.0162 0.0541 1.0000
4.750 0.5987 0.02002 0.01038 -0.0137 0.0475 1.0000
5.000 0.6170 0.02152 0.01189 -0.0115 0.0438 1.0000
5.250 0.6383 0.02333 0.01368 -0.0097 0.0420 1.0000
5.500 0.6627 0.02553 0.01593 -0.0084 0.0413 1.0000
5.750 0.6886 0.02782 0.01846 -0.0070 0.0422 1.0000
6.000 0.7128 0.03056 0.02169 -0.0050 0.0448 1.0000
6.250 0.7334 0.03338 0.02501 -0.0030 0.0454 1.0000
6.500 0.7513 0.03645 0.02853 -0.0009 0.0467 1.0000
6.750 0.7671 0.04019 0.03263 0.0010 0.0493 1.0000
7.000 0.7840 0.04514 0.03813 0.0036 0.0626 1.0000
9.250 0.5845 0.09059 0.08615 -0.0060 0.1608 1.0000
9.500 0.5919 0.09490 0.09044 -0.0050 0.1543 1.0000
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Polar data table (+)
Polar graphs
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