EPPLER E838 HYDROFOIL AIRFOIL (e838-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E838 HYDROFOIL AIRFOIL (e838-il) Reynolds number: 200,000 Max Cl/Cd: 51.1 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e838-il-200000.txt Download as CSV file: xf-e838-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E838 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6509 0.14132 0.13784 -0.0168 1.0000 0.0286
-16.500 -0.6799 0.12833 0.12483 -0.0237 1.0000 0.0276
-16.250 -0.7213 0.11415 0.11052 -0.0321 1.0000 0.0261
-16.000 -0.7675 0.10136 0.09748 -0.0394 1.0000 0.0252
-15.750 -0.8100 0.09100 0.08682 -0.0446 1.0000 0.0245
-15.500 -0.8710 0.08039 0.07562 -0.0489 1.0000 0.0231
-15.250 -0.8891 0.07553 0.07054 -0.0500 1.0000 0.0231
-15.000 -0.9027 0.07188 0.06668 -0.0505 1.0000 0.0228
-14.750 -0.9152 0.06816 0.06276 -0.0507 1.0000 0.0228
-14.500 -0.9291 0.06359 0.05795 -0.0506 1.0000 0.0229
-14.250 -0.9345 0.06109 0.05527 -0.0501 1.0000 0.0227
-14.000 -0.9376 0.05614 0.05010 -0.0497 1.0000 0.0234
-13.750 -0.9383 0.05329 0.04699 -0.0490 1.0000 0.0232
-13.500 -0.9282 0.05098 0.04470 -0.0488 1.0000 0.0244
-13.250 -0.9204 0.04881 0.04241 -0.0483 1.0000 0.0250
-13.000 -0.9108 0.04675 0.04021 -0.0477 1.0000 0.0257
-12.750 -0.8966 0.04464 0.03791 -0.0471 1.0000 0.0262
-12.500 -0.8794 0.04280 0.03589 -0.0465 1.0000 0.0270
-12.250 -0.8599 0.04124 0.03416 -0.0460 1.0000 0.0280
-12.000 -0.8408 0.03989 0.03266 -0.0454 1.0000 0.0289
-11.750 -0.8151 0.03857 0.03140 -0.0448 1.0000 0.0314
-11.500 -0.7994 0.03740 0.03024 -0.0443 1.0000 0.0335
-11.250 -0.7831 0.03629 0.02909 -0.0437 1.0000 0.0357
-11.000 -0.7667 0.03513 0.02790 -0.0429 1.0000 0.0379
-10.750 -0.7571 0.03366 0.02651 -0.0420 1.0000 0.0406
-10.500 -0.7459 0.03242 0.02528 -0.0417 1.0000 0.0442
-10.250 -0.7315 0.03069 0.02356 -0.0427 0.9696 0.0493
-10.000 -0.7064 0.02882 0.02161 -0.0459 0.9437 0.0583
-9.750 -0.6949 0.02680 0.01957 -0.0467 0.9224 0.0708
-9.500 -0.6963 0.02486 0.01773 -0.0451 0.9049 0.0894
-9.250 -0.7047 0.02293 0.01599 -0.0421 0.8907 0.1245
-9.000 -0.7163 0.02109 0.01439 -0.0385 0.8786 0.1691
-8.750 -0.7315 0.01932 0.01288 -0.0341 0.8676 0.2210
-8.500 -0.7489 0.01773 0.01156 -0.0289 0.8577 0.2746
-8.250 -0.7678 0.01655 0.01063 -0.0222 0.8499 0.3288
-8.000 -0.7837 0.01570 0.01018 -0.0155 0.8416 0.3952
-7.750 -0.7827 0.01532 0.01005 -0.0109 0.8360 0.4623
-7.500 -0.7698 0.01531 0.01010 -0.0083 0.8298 0.5052
-7.250 -0.7524 0.01545 0.01019 -0.0064 0.8247 0.5331
-7.000 -0.7308 0.01579 0.01045 -0.0049 0.8209 0.5535
-6.750 -0.7075 0.01627 0.01087 -0.0039 0.8157 0.5718
-6.500 -0.6825 0.01690 0.01143 -0.0029 0.8109 0.5877
-6.250 -0.6555 0.01740 0.01184 -0.0023 0.8071 0.5985
-6.000 -0.6327 0.01770 0.01201 -0.0014 0.8032 0.6091
-5.750 -0.5973 0.01860 0.01292 -0.0020 0.7989 0.6173
-5.500 -0.5685 0.01920 0.01345 -0.0016 0.7949 0.6264
-5.250 -0.5365 0.01988 0.01405 -0.0016 0.7916 0.6335
-5.000 -0.5116 0.02004 0.01412 -0.0012 0.7877 0.6403
-4.750 -0.4780 0.02056 0.01461 -0.0019 0.7837 0.6441
-4.500 -0.4597 0.02029 0.01421 -0.0008 0.7797 0.6519
-4.250 -0.4308 0.02039 0.01423 -0.0009 0.7766 0.6553
-4.000 -0.4003 0.02063 0.01443 -0.0013 0.7732 0.6581
-3.750 -0.3740 0.02067 0.01442 -0.0013 0.7689 0.6622
-3.500 -0.3573 0.02019 0.01381 -0.0003 0.7651 0.6691
-3.250 -0.3274 0.02028 0.01386 -0.0006 0.7621 0.6713
-3.000 -0.2988 0.02035 0.01386 -0.0008 0.7595 0.6741
-2.750 -0.2751 0.02029 0.01379 -0.0007 0.7547 0.6783
-2.500 -0.2564 0.01988 0.01327 0.0000 0.7508 0.6841
-2.250 -0.2277 0.01991 0.01327 -0.0003 0.7479 0.6863
-2.000 -0.1994 0.01993 0.01325 -0.0004 0.7453 0.6889
-1.750 -0.1748 0.01994 0.01325 -0.0003 0.7413 0.6926
-1.500 -0.1562 0.01959 0.01281 0.0002 0.7370 0.6986
-1.250 -0.1280 0.01962 0.01285 0.0000 0.7339 0.7007
-1.000 -0.0999 0.01964 0.01284 -0.0001 0.7313 0.7033
-0.750 -0.0727 0.01963 0.01280 -0.0002 0.7288 0.7064
-0.500 -0.0514 0.01963 0.01282 0.0000 0.7237 0.7108
-0.250 -0.0279 0.01952 0.01268 0.0001 0.7201 0.7149
0.000 0.0000 0.01954 0.01271 0.0000 0.7173 0.7173
0.250 0.0279 0.01952 0.01267 -0.0001 0.7149 0.7201
0.500 0.0514 0.01963 0.01282 0.0000 0.7107 0.7237
0.750 0.0726 0.01963 0.01279 0.0002 0.7064 0.7289
1.000 0.0999 0.01964 0.01285 0.0001 0.7033 0.7313
1.250 0.1280 0.01962 0.01285 0.0000 0.7007 0.7340
1.500 0.1562 0.01960 0.01281 -0.0002 0.6986 0.7371
1.750 0.1747 0.01994 0.01325 0.0004 0.6927 0.7414
2.000 0.1994 0.01993 0.01325 0.0004 0.6889 0.7454
2.250 0.2277 0.01991 0.01328 0.0003 0.6863 0.7479
2.500 0.2563 0.01989 0.01328 0.0000 0.6842 0.7509
2.750 0.2750 0.02029 0.01379 0.0007 0.6783 0.7548
3.000 0.2987 0.02036 0.01387 0.0008 0.6741 0.7595
3.250 0.3272 0.02029 0.01387 0.0006 0.6714 0.7621
3.500 0.3572 0.02019 0.01382 0.0004 0.6691 0.7651
3.750 0.3739 0.02067 0.01443 0.0014 0.6623 0.7690
4.000 0.4001 0.02064 0.01443 0.0013 0.6581 0.7733
4.250 0.4306 0.02040 0.01424 0.0009 0.6553 0.7767
4.500 0.4632 0.02015 0.01404 0.0004 0.6530 0.7797
4.750 0.4778 0.02056 0.01462 0.0019 0.6441 0.7838
5.000 0.5114 0.02005 0.01413 0.0012 0.6404 0.7878
5.250 0.5365 0.01988 0.01405 0.0017 0.6336 0.7917
5.500 0.5683 0.01922 0.01346 0.0016 0.6265 0.7949
5.750 0.5973 0.01860 0.01292 0.0020 0.6173 0.7990
6.000 0.6326 0.01770 0.01200 0.0014 0.6091 0.8033
6.250 0.6553 0.01741 0.01185 0.0023 0.5986 0.8072
6.500 0.6824 0.01690 0.01143 0.0029 0.5877 0.8109
6.750 0.7074 0.01626 0.01087 0.0039 0.5717 0.8158
7.000 0.7307 0.01577 0.01043 0.0050 0.5532 0.8209
7.250 0.7523 0.01545 0.01019 0.0064 0.5330 0.8248
7.500 0.7697 0.01531 0.01010 0.0084 0.5053 0.8299
7.750 0.7828 0.01532 0.01006 0.0109 0.4630 0.8360
8.000 0.7832 0.01571 0.01018 0.0155 0.3943 0.8417
8.250 0.7683 0.01653 0.01063 0.0221 0.3295 0.8499
8.500 0.7489 0.01772 0.01156 0.0289 0.2746 0.8578
8.750 0.7324 0.01927 0.01285 0.0340 0.2228 0.8677
9.000 0.7164 0.02108 0.01438 0.0385 0.1691 0.8788
9.250 0.7041 0.02296 0.01601 0.0422 0.1234 0.8908
9.500 0.6967 0.02485 0.01772 0.0450 0.0899 0.9050
9.750 0.6958 0.02675 0.01953 0.0466 0.0711 0.9224
10.000 0.7063 0.02887 0.02166 0.0458 0.0581 0.9441
10.500 0.7463 0.03240 0.02526 0.0416 0.0445 1.0000
10.750 0.7578 0.03363 0.02648 0.0420 0.0407 1.0000
11.000 0.7674 0.03511 0.02788 0.0429 0.0379 1.0000
11.250 0.7838 0.03626 0.02906 0.0436 0.0357 1.0000
11.500 0.7994 0.03740 0.03025 0.0442 0.0332 1.0000
11.750 0.8140 0.03860 0.03141 0.0447 0.0310 1.0000
12.000 0.8404 0.03989 0.03267 0.0453 0.0288 1.0000
12.250 0.8601 0.04122 0.03414 0.0459 0.0279 1.0000
12.500 0.8799 0.04278 0.03586 0.0465 0.0270 1.0000
12.750 0.8980 0.04461 0.03788 0.0470 0.0264 1.0000
13.000 0.9117 0.04673 0.04019 0.0477 0.0257 1.0000
13.250 0.9215 0.04869 0.04225 0.0482 0.0247 1.0000
13.500 0.9284 0.05081 0.04448 0.0487 0.0241 1.0000
13.750 0.9335 0.05337 0.04722 0.0493 0.0239 1.0000
14.000 0.9417 0.05656 0.05047 0.0495 0.0230 1.0000
14.500 0.9217 0.06471 0.05912 0.0505 0.0226 1.0000
14.750 0.9160 0.06810 0.06270 0.0506 0.0228 1.0000
15.000 0.9028 0.07207 0.06688 0.0504 0.0228 1.0000
15.250 0.8895 0.07575 0.07076 0.0498 0.0230 1.0000
15.500 0.8718 0.08025 0.07549 0.0487 0.0232 1.0000
15.750 0.8506 0.08583 0.08129 0.0470 0.0233 1.0000
16.000 0.7615 0.10264 0.09880 0.0387 0.0255 1.0000
16.250 0.7203 0.11464 0.11101 0.0317 0.0263 1.0000
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Polar data table (+)
Polar graphs
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