EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Reynolds number: 50,000 Max Cl/Cd: 26.56 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e837-il-50000.txt Download as CSV file: xf-e837-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7779 0.09190 0.08509 -0.0404 1.0000 0.1017
-12.750 -0.7926 0.08602 0.07914 -0.0421 1.0000 0.1009
-12.500 -0.8141 0.08045 0.07346 -0.0435 1.0000 0.1001
-12.250 -0.8351 0.07545 0.06833 -0.0442 1.0000 0.0993
-12.000 -0.8578 0.07096 0.06367 -0.0440 1.0000 0.0987
-11.750 -0.8769 0.06700 0.05951 -0.0431 1.0000 0.0982
-11.500 -0.8952 0.06337 0.05563 -0.0412 1.0000 0.0981
-11.250 -0.9096 0.06006 0.05206 -0.0387 1.0000 0.0981
-11.000 -0.9196 0.05684 0.04853 -0.0359 1.0000 0.0987
-10.750 -0.9239 0.05372 0.04502 -0.0334 1.0000 0.0999
-10.500 -0.9218 0.05049 0.04146 -0.0313 1.0000 0.1030
-10.250 -0.8994 0.04751 0.03848 -0.0311 1.0000 0.1105
-10.000 -0.8843 0.04438 0.03495 -0.0298 1.0000 0.1165
-9.750 -0.8627 0.04182 0.03225 -0.0291 1.0000 0.1288
-9.500 -0.8169 0.03864 0.02934 -0.0309 1.0000 0.1545
-9.250 -0.7906 0.03608 0.02718 -0.0304 1.0000 0.1919
-9.000 -0.7876 0.03391 0.02548 -0.0273 1.0000 0.2341
-8.750 -0.7961 0.03206 0.02423 -0.0227 1.0000 0.2813
-8.500 -0.8073 0.03072 0.02360 -0.0170 1.0000 0.3388
-8.250 -0.8147 0.03070 0.02420 -0.0105 1.0000 0.4020
-8.000 -0.7470 0.03822 0.03183 -0.0058 1.0000 0.4872
-7.750 -0.5678 0.05318 0.04559 -0.0056 1.0000 0.5351
-7.500 -0.5075 0.05582 0.04782 -0.0048 1.0000 0.5606
-7.250 -0.4889 0.05559 0.04746 -0.0031 1.0000 0.5837
-7.000 -0.4485 0.05607 0.04769 -0.0029 1.0000 0.6065
-6.750 -0.4377 0.05539 0.04692 -0.0010 1.0000 0.6273
-6.500 -0.3969 0.05531 0.04664 -0.0015 1.0000 0.6481
-6.250 -0.3866 0.05473 0.04601 0.0004 1.0000 0.6672
-6.000 -0.3880 0.05428 0.04556 0.0039 1.0000 0.6839
-5.750 -0.3909 0.05398 0.04524 0.0076 1.0000 0.6991
-5.500 -0.3931 0.05366 0.04486 0.0113 1.0000 0.7142
-5.250 -0.3922 0.05326 0.04441 0.0144 1.0000 0.7293
-5.000 -0.3888 0.05280 0.04389 0.0171 1.0000 0.7444
-4.750 -0.3822 0.05228 0.04329 0.0192 1.0000 0.7591
-4.500 -0.3732 0.05171 0.04264 0.0209 1.0000 0.7735
-4.250 -0.3627 0.05113 0.04198 0.0223 1.0000 0.7876
-4.000 -0.3520 0.05051 0.04126 0.0234 1.0000 0.8008
-3.750 -0.3434 0.04987 0.04056 0.0248 1.0000 0.8134
-3.500 -0.3404 0.04924 0.03987 0.0269 1.0000 0.8252
-3.250 -0.3495 0.04866 0.03924 0.0307 1.0000 0.8360
-3.000 -0.3242 0.04804 0.03853 0.0294 1.0000 0.8473
-2.750 -0.3113 0.04744 0.03784 0.0298 1.0000 0.8577
-2.500 -0.3153 0.04686 0.03722 0.0328 1.0000 0.8674
-2.250 -0.2955 0.04634 0.03663 0.0321 1.0000 0.8773
-2.000 -0.2823 0.04582 0.03605 0.0323 1.0000 0.8863
-1.750 -0.2827 0.04535 0.03553 0.0347 0.9997 0.8954
-1.500 -0.2239 0.04512 0.03518 0.0266 0.9930 0.9047
-1.250 -0.1904 0.04485 0.03485 0.0228 0.9862 0.9134
-1.000 -0.1475 0.04468 0.03460 0.0174 0.9795 0.9219
-0.750 -0.1088 0.04449 0.03437 0.0127 0.9726 0.9296
-0.500 -0.0740 0.04440 0.03424 0.0087 0.9661 0.9375
-0.250 -0.0363 0.04429 0.03411 0.0042 0.9589 0.9445
0.000 -0.0001 0.04431 0.03412 0.0000 0.9523 0.9522
0.250 0.0353 0.04429 0.03411 -0.0040 0.9447 0.9588
0.500 0.0743 0.04439 0.03424 -0.0088 0.9374 0.9661
0.750 0.1094 0.04448 0.03436 -0.0128 0.9296 0.9727
1.000 0.1476 0.04467 0.03459 -0.0174 0.9220 0.9796
1.250 0.1899 0.04484 0.03484 -0.0227 0.9134 0.9862
1.500 0.2239 0.04511 0.03517 -0.0266 0.9047 0.9930
1.750 0.2824 0.04534 0.03552 -0.0346 0.8954 0.9997
2.000 0.2822 0.04581 0.03604 -0.0323 0.8863 1.0000
2.250 0.2956 0.04632 0.03661 -0.0321 0.8773 1.0000
2.500 0.3155 0.04684 0.03720 -0.0329 0.8674 1.0000
2.750 0.3111 0.04742 0.03782 -0.0298 0.8578 1.0000
3.000 0.3243 0.04802 0.03851 -0.0294 0.8473 1.0000
3.250 0.3499 0.04863 0.03921 -0.0308 0.8360 1.0000
3.500 0.3404 0.04922 0.03984 -0.0269 0.8252 1.0000
3.750 0.3436 0.04984 0.04052 -0.0248 0.8133 1.0000
4.000 0.3521 0.05047 0.04122 -0.0234 0.8009 1.0000
4.250 0.3628 0.05109 0.04194 -0.0223 0.7875 1.0000
4.500 0.3739 0.05170 0.04263 -0.0210 0.7738 1.0000
4.750 0.3825 0.05225 0.04326 -0.0193 0.7592 1.0000
5.000 0.3893 0.05278 0.04386 -0.0172 0.7445 1.0000
5.250 0.3925 0.05323 0.04437 -0.0145 0.7294 1.0000
5.500 0.3931 0.05362 0.04482 -0.0113 0.7142 1.0000
5.750 0.3912 0.05393 0.04519 -0.0077 0.6991 1.0000
6.000 0.3883 0.05424 0.04552 -0.0039 0.6839 1.0000
6.250 0.3867 0.05469 0.04597 -0.0004 0.6671 1.0000
6.500 0.3972 0.05527 0.04660 0.0015 0.6482 1.0000
6.750 0.4401 0.05530 0.04684 0.0009 0.6271 1.0000
7.000 0.4489 0.05603 0.04765 0.0028 0.6064 1.0000
7.250 0.4894 0.05557 0.04743 0.0031 0.5837 1.0000
7.500 0.5080 0.05579 0.04779 0.0048 0.5605 1.0000
7.750 0.5685 0.05314 0.04556 0.0056 0.5351 1.0000
8.250 0.8148 0.03068 0.02418 0.0105 0.4022 1.0000
8.500 0.8073 0.03072 0.02359 0.0170 0.3388 1.0000
8.750 0.7966 0.03206 0.02422 0.0226 0.2814 1.0000
9.000 0.7877 0.03390 0.02547 0.0273 0.2340 1.0000
9.250 0.7902 0.03607 0.02717 0.0304 0.1917 1.0000
9.500 0.8169 0.03864 0.02934 0.0309 0.1544 1.0000
9.750 0.8627 0.04184 0.03228 0.0291 0.1286 1.0000
10.000 0.8836 0.04434 0.03492 0.0299 0.1167 1.0000
10.250 0.9001 0.04753 0.03850 0.0310 0.1107 1.0000
10.500 0.9209 0.05044 0.04144 0.0314 0.1033 1.0000
10.750 0.9247 0.05377 0.04507 0.0333 0.0999 1.0000
11.000 0.9199 0.05687 0.04856 0.0359 0.0987 1.0000
11.250 0.9106 0.06008 0.05209 0.0386 0.0982 1.0000
11.500 0.8960 0.06339 0.05565 0.0411 0.0981 1.0000
11.750 0.8778 0.06700 0.05951 0.0430 0.0982 1.0000
12.000 0.8584 0.07099 0.06369 0.0439 0.0987 1.0000
12.250 0.8349 0.07550 0.06838 0.0441 0.0992 1.0000
12.500 0.8138 0.08051 0.07353 0.0434 0.1001 1.0000
12.750 0.7924 0.08612 0.07924 0.0419 0.1008 1.0000
13.000 0.7787 0.09199 0.08517 0.0403 0.1017 1.0000
13.250 0.6304 0.12006 0.11324 0.0190 0.1268 1.0000
13.500 0.6299 0.12629 0.11944 0.0169 0.1283 1.0000
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