EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Reynolds number: 50,000 Max Cl/Cd: 29.87 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e874-il-50000-n5.txt Download as CSV file: xf-e874-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5864 0.09521 0.08842 -0.0081 1.0000 0.0309
-9.000 -0.5901 0.09011 0.08341 -0.0108 1.0000 0.0306
-8.750 -0.5951 0.08472 0.07811 -0.0140 1.0000 0.0301
-8.500 -0.6016 0.07898 0.07246 -0.0180 1.0000 0.0295
-8.250 -0.6115 0.07281 0.06633 -0.0218 1.0000 0.0289
-8.000 -0.6210 0.06706 0.06051 -0.0245 1.0000 0.0283
-7.750 -0.6287 0.06156 0.05485 -0.0261 1.0000 0.0279
-7.500 -0.6328 0.05636 0.04936 -0.0268 1.0000 0.0274
-7.250 -0.6325 0.05153 0.04415 -0.0267 1.0000 0.0271
-7.000 -0.6271 0.04731 0.03950 -0.0259 1.0000 0.0272
-6.750 -0.6177 0.04365 0.03542 -0.0248 1.0000 0.0278
-6.500 -0.6053 0.04048 0.03186 -0.0236 1.0000 0.0292
-6.250 -0.5904 0.03752 0.02832 -0.0223 1.0000 0.0311
-6.000 -0.5729 0.03463 0.02488 -0.0207 1.0000 0.0335
-5.750 -0.5529 0.03207 0.02181 -0.0192 1.0000 0.0350
-5.500 -0.5319 0.02970 0.01907 -0.0176 1.0000 0.0366
-5.250 -0.5126 0.02748 0.01671 -0.0161 1.0000 0.0396
-5.000 -0.4915 0.02588 0.01479 -0.0146 1.0000 0.0480
-4.750 -0.4712 0.02403 0.01287 -0.0131 1.0000 0.0602
-4.500 -0.4496 0.02206 0.01127 -0.0121 1.0000 0.1011
-4.250 -0.4281 0.02073 0.01041 -0.0113 1.0000 0.2203
-4.000 -0.4093 0.02016 0.01001 -0.0100 1.0000 0.2946
-3.750 -0.3862 0.01944 0.00911 -0.0089 1.0000 0.3337
-3.500 -0.3629 0.01874 0.00836 -0.0079 1.0000 0.3719
-3.250 -0.3405 0.01803 0.00771 -0.0068 1.0000 0.4187
-3.000 -0.3191 0.01733 0.00717 -0.0053 1.0000 0.4810
-2.750 -0.2986 0.01661 0.00674 -0.0035 1.0000 0.5634
-2.500 -0.2754 0.01588 0.00636 -0.0016 1.0000 0.6784
-2.250 -0.1943 0.01544 0.00608 -0.0104 1.0000 0.8895
-2.000 -0.1144 0.01549 0.00563 -0.0209 1.0000 1.0000
-1.750 -0.0966 0.01537 0.00524 -0.0194 1.0000 1.0000
-1.500 -0.0783 0.01529 0.00499 -0.0180 1.0000 1.0000
-1.250 -0.0597 0.01524 0.00480 -0.0166 1.0000 1.0000
-1.000 -0.0411 0.01522 0.00467 -0.0152 1.0000 1.0000
-0.750 -0.0228 0.01524 0.00459 -0.0137 1.0000 1.0000
-0.500 -0.0048 0.01529 0.00456 -0.0122 1.0000 1.0000
-0.250 0.0124 0.01538 0.00460 -0.0107 1.0000 1.0000
0.000 0.0286 0.01552 0.00472 -0.0091 1.0000 1.0000
0.250 0.0523 0.01571 0.00491 -0.0092 0.9944 1.0000
0.500 0.1014 0.01580 0.00504 -0.0142 0.9626 1.0000
0.750 0.1500 0.01586 0.00515 -0.0187 0.9329 1.0000
1.000 0.2004 0.01590 0.00525 -0.0234 0.9031 1.0000
1.250 0.2480 0.01595 0.00537 -0.0273 0.8711 1.0000
1.500 0.2925 0.01603 0.00555 -0.0304 0.8388 1.0000
1.750 0.3304 0.01618 0.00573 -0.0321 0.8071 1.0000
2.000 0.3620 0.01641 0.00598 -0.0325 0.7776 1.0000
2.250 0.3905 0.01670 0.00630 -0.0322 0.7510 1.0000
2.500 0.4173 0.01702 0.00676 -0.0317 0.7274 1.0000
2.750 0.4427 0.01738 0.00723 -0.0310 0.7053 1.0000
3.000 0.4684 0.01776 0.00773 -0.0303 0.6862 1.0000
3.250 0.4933 0.01816 0.00832 -0.0295 0.6673 1.0000
3.500 0.5182 0.01858 0.00896 -0.0287 0.6493 1.0000
3.750 0.5430 0.01901 0.00964 -0.0278 0.6319 1.0000
4.000 0.5675 0.01945 0.01050 -0.0267 0.6128 1.0000
4.250 0.5828 0.01951 0.01057 -0.0227 0.5585 1.0000
4.500 0.5843 0.01957 0.00992 -0.0159 0.4123 1.0000
4.750 0.5879 0.02289 0.01110 -0.0128 0.0857 1.0000
5.000 0.6043 0.02505 0.01318 -0.0109 0.0591 1.0000
5.250 0.6209 0.02668 0.01492 -0.0091 0.0463 1.0000
5.500 0.6373 0.02835 0.01671 -0.0072 0.0412 1.0000
5.750 0.6549 0.03021 0.01870 -0.0051 0.0380 1.0000
6.000 0.6764 0.03187 0.02064 -0.0034 0.0336 1.0000
6.250 0.6973 0.03381 0.02286 -0.0021 0.0300 1.0000
6.500 0.7187 0.03643 0.02564 -0.0009 0.0284 1.0000
6.750 0.7395 0.03977 0.02919 0.0004 0.0277 1.0000
7.000 0.7580 0.04266 0.03254 0.0019 0.0274 1.0000
7.250 0.7732 0.04584 0.03618 0.0036 0.0272 1.0000
7.500 0.7852 0.04922 0.03999 0.0052 0.0271 1.0000
7.750 0.7939 0.05275 0.04393 0.0068 0.0271 1.0000
8.000 0.7991 0.05653 0.04807 0.0083 0.0272 1.0000
8.250 0.8020 0.06032 0.05217 0.0096 0.0274 1.0000
8.500 0.8019 0.06430 0.05641 0.0108 0.0276 1.0000
9.000 0.7925 0.07153 0.06419 0.0126 0.0281 1.0000
9.250 0.7801 0.07481 0.06768 0.0133 0.0285 1.0000
9.500 0.7621 0.07882 0.07183 0.0125 0.0288 1.0000
9.750 0.7407 0.08452 0.07766 0.0081 0.0294 1.0000
10.000 0.7229 0.09198 0.08514 0.0021 0.0300 1.0000
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Polar data table (+)
Polar graphs
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