EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Reynolds number: 200,000 Max Cl/Cd: 50.3 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e837-il-200000-n5.txt Download as CSV file: xf-e837-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E837 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8325 0.12574 0.12164 -0.0072 1.0000 0.0091
-17.250 -0.8509 0.11698 0.11270 -0.0124 1.0000 0.0091
-17.000 -0.8681 0.10893 0.10445 -0.0170 1.0000 0.0091
-16.750 -0.8825 0.10187 0.09722 -0.0209 1.0000 0.0091
-16.500 -0.8934 0.09568 0.09083 -0.0242 1.0000 0.0090
-16.250 -0.9047 0.08984 0.08485 -0.0271 1.0000 0.0091
-16.000 -0.9130 0.08468 0.07953 -0.0295 1.0000 0.0092
-15.750 -0.9197 0.07997 0.07469 -0.0316 1.0000 0.0093
-15.500 -0.9259 0.07550 0.07006 -0.0333 1.0000 0.0094
-15.250 -0.9302 0.07150 0.06595 -0.0349 1.0000 0.0096
-15.000 -0.9330 0.06779 0.06209 -0.0360 1.0000 0.0097
-14.750 -0.9348 0.06436 0.05853 -0.0369 1.0000 0.0098
-14.500 -0.9352 0.06121 0.05525 -0.0376 1.0000 0.0100
-14.250 -0.9349 0.05825 0.05217 -0.0382 1.0000 0.0103
-14.000 -0.9330 0.05558 0.04937 -0.0386 1.0000 0.0108
-13.750 -0.9305 0.05304 0.04669 -0.0387 1.0000 0.0113
-13.500 -0.9267 0.05068 0.04417 -0.0387 1.0000 0.0118
-13.250 -0.9215 0.04851 0.04187 -0.0385 1.0000 0.0121
-13.000 -0.9158 0.04645 0.03965 -0.0382 1.0000 0.0124
-12.750 -0.9127 0.04419 0.03732 -0.0377 1.0000 0.0129
-12.500 -0.9093 0.04205 0.03513 -0.0372 1.0000 0.0134
-12.250 -0.9043 0.04012 0.03313 -0.0367 1.0000 0.0139
-12.000 -0.8982 0.03834 0.03128 -0.0361 1.0000 0.0143
-11.750 -0.8918 0.03662 0.02948 -0.0354 1.0000 0.0151
-11.500 -0.8860 0.03488 0.02765 -0.0346 1.0000 0.0157
-11.250 -0.8784 0.03334 0.02600 -0.0338 1.0000 0.0167
-11.000 -0.8733 0.03165 0.02426 -0.0328 1.0000 0.0177
-10.750 -0.8674 0.03009 0.02267 -0.0318 1.0000 0.0190
-10.500 -0.8589 0.02876 0.02128 -0.0308 1.0000 0.0204
-10.250 -0.8493 0.02755 0.01998 -0.0298 1.0000 0.0224
-10.000 -0.8434 0.02614 0.01853 -0.0284 1.0000 0.0244
-9.750 -0.8353 0.02493 0.01730 -0.0270 1.0000 0.0266
-9.500 -0.8254 0.02391 0.01622 -0.0257 1.0000 0.0297
-9.250 -0.8155 0.02278 0.01511 -0.0246 0.9782 0.0342
-9.000 -0.7880 0.02155 0.01383 -0.0269 0.9289 0.0436
-8.750 -0.7710 0.02049 0.01274 -0.0267 0.8999 0.0562
-8.500 -0.7610 0.01961 0.01185 -0.0248 0.8784 0.0711
-8.250 -0.7524 0.01885 0.01106 -0.0224 0.8620 0.0888
-8.000 -0.7463 0.01813 0.01039 -0.0194 0.8487 0.1111
-7.750 -0.7375 0.01741 0.00974 -0.0168 0.8378 0.1384
-7.500 -0.7263 0.01670 0.00913 -0.0146 0.8277 0.1692
-7.250 -0.7145 0.01600 0.00853 -0.0124 0.8191 0.2033
-7.000 -0.7032 0.01525 0.00794 -0.0102 0.8111 0.2471
-6.750 -0.6926 0.01443 0.00737 -0.0078 0.8036 0.3031
-6.500 -0.6812 0.01368 0.00689 -0.0055 0.7966 0.3660
-6.250 -0.6645 0.01321 0.00660 -0.0038 0.7904 0.4177
-6.000 -0.6433 0.01294 0.00640 -0.0027 0.7842 0.4529
-5.500 -0.5966 0.01267 0.00612 -0.0012 0.7731 0.5059
-5.250 -0.5717 0.01260 0.00598 -0.0007 0.7679 0.5239
-5.000 -0.5463 0.01256 0.00586 -0.0003 0.7633 0.5388
-4.750 -0.5202 0.01252 0.00577 0.0000 0.7577 0.5520
-4.500 -0.4941 0.01249 0.00566 0.0003 0.7529 0.5638
-4.250 -0.4677 0.01247 0.00551 0.0005 0.7486 0.5747
-4.000 -0.4407 0.01246 0.00547 0.0006 0.7435 0.5834
-3.750 -0.4138 0.01244 0.00537 0.0008 0.7388 0.5918
-3.250 -0.3596 0.01243 0.00523 0.0009 0.7299 0.6074
-3.000 -0.3325 0.01241 0.00514 0.0010 0.7253 0.6147
-2.750 -0.3050 0.01240 0.00506 0.0010 0.7214 0.6207
-2.500 -0.2774 0.01239 0.00501 0.0009 0.7170 0.6266
-2.250 -0.2501 0.01237 0.00492 0.0009 0.7124 0.6329
-2.000 -0.2223 0.01236 0.00490 0.0009 0.7083 0.6376
-1.750 -0.1947 0.01235 0.00481 0.0008 0.7046 0.6433
-1.500 -0.1670 0.01233 0.00477 0.0007 0.6999 0.6482
-1.250 -0.1391 0.01232 0.00476 0.0006 0.6955 0.6524
-1.000 -0.1113 0.01231 0.00469 0.0005 0.6918 0.6573
-0.750 -0.0837 0.01230 0.00465 0.0004 0.6875 0.6621
-0.500 -0.0557 0.01229 0.00467 0.0002 0.6829 0.6658
-0.250 -0.0278 0.01229 0.00465 0.0001 0.6789 0.6703
0.000 0.0000 0.01229 0.00459 0.0000 0.6752 0.6752
0.250 0.0278 0.01229 0.00465 -0.0001 0.6703 0.6788
0.500 0.0557 0.01229 0.00467 -0.0002 0.6658 0.6829
0.750 0.0837 0.01230 0.00465 -0.0004 0.6621 0.6875
1.000 0.1113 0.01231 0.00469 -0.0005 0.6573 0.6918
1.250 0.1391 0.01232 0.00476 -0.0006 0.6524 0.6955
1.500 0.1670 0.01233 0.00477 -0.0007 0.6482 0.6999
1.750 0.1947 0.01235 0.00481 -0.0008 0.6432 0.7046
2.000 0.2223 0.01236 0.00489 -0.0009 0.6376 0.7083
2.250 0.2501 0.01237 0.00492 -0.0009 0.6329 0.7124
2.500 0.2775 0.01239 0.00501 -0.0010 0.6267 0.7171
2.750 0.3050 0.01240 0.00506 -0.0010 0.6207 0.7214
3.000 0.3325 0.01241 0.00514 -0.0010 0.6147 0.7253
3.250 0.3596 0.01243 0.00523 -0.0009 0.6074 0.7300
3.750 0.4139 0.01244 0.00537 -0.0008 0.5918 0.7388
4.000 0.4407 0.01246 0.00547 -0.0006 0.5834 0.7435
4.250 0.4678 0.01247 0.00551 -0.0005 0.5747 0.7486
4.500 0.4941 0.01250 0.00566 -0.0003 0.5638 0.7529
4.750 0.5203 0.01252 0.00576 0.0000 0.5520 0.7577
5.000 0.5463 0.01256 0.00585 0.0002 0.5388 0.7633
5.250 0.5718 0.01260 0.00598 0.0007 0.5239 0.7678
5.500 0.5967 0.01267 0.00612 0.0012 0.5060 0.7731
6.000 0.6434 0.01294 0.00640 0.0027 0.4529 0.7842
6.250 0.6645 0.01321 0.00660 0.0038 0.4175 0.7904
6.500 0.6813 0.01368 0.00689 0.0055 0.3660 0.7966
6.750 0.6929 0.01442 0.00737 0.0078 0.3038 0.8036
7.000 0.7030 0.01527 0.00795 0.0102 0.2455 0.8111
7.250 0.7144 0.01602 0.00854 0.0124 0.2022 0.8191
7.500 0.7264 0.01671 0.00913 0.0145 0.1689 0.8276
7.750 0.7378 0.01741 0.00974 0.0167 0.1386 0.8378
8.000 0.7468 0.01812 0.01039 0.0193 0.1114 0.8487
8.250 0.7531 0.01883 0.01106 0.0223 0.0892 0.8620
8.500 0.7612 0.01962 0.01185 0.0248 0.0705 0.8785
8.750 0.7715 0.02049 0.01274 0.0267 0.0561 0.8999
9.000 0.7886 0.02155 0.01383 0.0268 0.0437 0.9289
9.250 0.8160 0.02279 0.01510 0.0245 0.0336 0.9785
9.500 0.8259 0.02391 0.01622 0.0256 0.0298 1.0000
9.750 0.8360 0.02492 0.01729 0.0269 0.0268 1.0000
10.000 0.8439 0.02615 0.01853 0.0283 0.0243 1.0000
10.250 0.8501 0.02755 0.01997 0.0296 0.0224 1.0000
10.500 0.8586 0.02883 0.02136 0.0308 0.0210 1.0000
10.750 0.8680 0.03010 0.02267 0.0317 0.0187 1.0000
11.000 0.8740 0.03166 0.02426 0.0327 0.0175 1.0000
11.250 0.8796 0.03332 0.02599 0.0336 0.0166 1.0000
11.500 0.8868 0.03489 0.02766 0.0345 0.0158 1.0000
11.750 0.8930 0.03660 0.02945 0.0353 0.0150 1.0000
12.000 0.8991 0.03835 0.03129 0.0360 0.0143 1.0000
12.250 0.9052 0.04014 0.03314 0.0365 0.0138 1.0000
12.500 0.9100 0.04209 0.03515 0.0370 0.0133 1.0000
12.750 0.9138 0.04419 0.03732 0.0375 0.0129 1.0000
13.000 0.9172 0.04643 0.03965 0.0380 0.0124 1.0000
13.250 0.9230 0.04849 0.04184 0.0384 0.0122 1.0000
13.500 0.9278 0.05071 0.04421 0.0386 0.0117 1.0000
13.750 0.9318 0.05305 0.04670 0.0386 0.0113 1.0000
14.000 0.9347 0.05553 0.04931 0.0383 0.0107 1.0000
14.250 0.9366 0.05821 0.05213 0.0380 0.0104 1.0000
14.500 0.9374 0.06111 0.05515 0.0374 0.0101 1.0000
14.750 0.9360 0.06440 0.05858 0.0368 0.0099 1.0000
15.000 0.9345 0.06778 0.06207 0.0357 0.0096 1.0000
15.250 0.9316 0.07150 0.06593 0.0346 0.0095 1.0000
15.500 0.9272 0.07555 0.07013 0.0332 0.0094 1.0000
15.750 0.9216 0.07989 0.07459 0.0314 0.0092 1.0000
16.000 0.9142 0.08477 0.07965 0.0293 0.0093 1.0000
16.250 0.9063 0.08988 0.08490 0.0269 0.0092 1.0000
16.500 0.8960 0.09557 0.09073 0.0240 0.0090 1.0000
16.750 0.8835 0.10196 0.09729 0.0206 0.0090 1.0000
17.000 0.8699 0.10899 0.10452 0.0167 0.0091 1.0000
17.250 0.8539 0.11674 0.11246 0.0122 0.0091 1.0000
17.500 0.8335 0.12598 0.12189 0.0068 0.0091 1.0000
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