EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Reynolds number: 200,000 Max Cl/Cd: 53 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e837-il-200000.txt Download as CSV file: xf-e837-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7813 0.10508 0.10119 -0.0262 1.0000 0.0244
-15.250 -0.8018 0.09723 0.09323 -0.0304 1.0000 0.0239
-15.000 -0.8230 0.09002 0.08587 -0.0343 1.0000 0.0236
-14.750 -0.8468 0.08305 0.07872 -0.0378 1.0000 0.0235
-14.500 -0.8674 0.07707 0.07255 -0.0404 1.0000 0.0233
-14.250 -0.8851 0.07184 0.06713 -0.0421 1.0000 0.0230
-14.000 -0.9038 0.06679 0.06186 -0.0433 1.0000 0.0229
-13.750 -0.9201 0.06220 0.05703 -0.0439 1.0000 0.0228
-13.500 -0.9330 0.05824 0.05284 -0.0440 1.0000 0.0229
-13.250 -0.9419 0.05452 0.04888 -0.0437 1.0000 0.0226
-13.000 -0.9491 0.05132 0.04543 -0.0431 1.0000 0.0230
-12.750 -0.9511 0.04826 0.04213 -0.0422 1.0000 0.0230
-12.500 -0.9524 0.04592 0.03956 -0.0412 1.0000 0.0237
-12.250 -0.9500 0.04366 0.03706 -0.0401 1.0000 0.0241
-12.000 -0.9490 0.04193 0.03509 -0.0387 1.0000 0.0246
-11.750 -0.9284 0.03883 0.03178 -0.0382 1.0000 0.0253
-11.500 -0.9043 0.03670 0.02961 -0.0378 1.0000 0.0265
-11.250 -0.8872 0.03518 0.02805 -0.0370 1.0000 0.0276
-11.000 -0.8706 0.03377 0.02655 -0.0362 1.0000 0.0290
-10.750 -0.8540 0.03245 0.02516 -0.0352 1.0000 0.0303
-10.500 -0.8401 0.03135 0.02392 -0.0343 1.0000 0.0322
-10.250 -0.8296 0.02951 0.02218 -0.0328 1.0000 0.0349
-10.000 -0.8195 0.02823 0.02090 -0.0316 1.0000 0.0379
-9.750 -0.8085 0.02700 0.01959 -0.0303 1.0000 0.0408
-9.500 -0.8071 0.02522 0.01786 -0.0282 1.0000 0.0440
-9.250 -0.7990 0.02405 0.01669 -0.0267 1.0000 0.0498
-9.000 -0.7985 0.02256 0.01523 -0.0243 1.0000 0.0555
-8.750 -0.7976 0.02142 0.01413 -0.0216 1.0000 0.0645
-8.500 -0.8050 0.02045 0.01329 -0.0179 0.9911 0.0770
-8.250 -0.7859 0.01812 0.01143 -0.0200 0.9698 0.1391
-8.000 -0.7684 0.01647 0.01018 -0.0206 0.9513 0.2136
-7.750 -0.7549 0.01525 0.00929 -0.0196 0.9349 0.2807
-7.500 -0.7445 0.01440 0.00870 -0.0173 0.9202 0.3416
-7.250 -0.7335 0.01384 0.00834 -0.0146 0.9078 0.3993
-7.000 -0.7184 0.01356 0.00817 -0.0124 0.8973 0.4480
-6.750 -0.7006 0.01347 0.00816 -0.0105 0.8873 0.4876
-6.500 -0.6807 0.01355 0.00820 -0.0088 0.8792 0.5192
-6.250 -0.6585 0.01368 0.00829 -0.0076 0.8707 0.5418
-6.000 -0.6348 0.01383 0.00834 -0.0065 0.8640 0.5586
-5.750 -0.6106 0.01402 0.00845 -0.0057 0.8565 0.5741
-5.500 -0.5858 0.01423 0.00856 -0.0048 0.8506 0.5876
-5.250 -0.5606 0.01438 0.00864 -0.0042 0.8434 0.5994
-5.000 -0.5363 0.01452 0.00862 -0.0034 0.8378 0.6111
-4.750 -0.5079 0.01476 0.00887 -0.0032 0.8316 0.6192
-4.500 -0.4824 0.01486 0.00888 -0.0027 0.8255 0.6287
-4.250 -0.4554 0.01503 0.00895 -0.0022 0.8210 0.6369
-4.000 -0.4288 0.01511 0.00899 -0.0021 0.8145 0.6444
-3.750 -0.4020 0.01521 0.00903 -0.0017 0.8093 0.6518
-3.500 -0.3756 0.01528 0.00902 -0.0014 0.8044 0.6589
-3.250 -0.3481 0.01539 0.00911 -0.0013 0.7986 0.6654
-3.000 -0.3226 0.01537 0.00898 -0.0010 0.7938 0.6726
-2.750 -0.2945 0.01548 0.00908 -0.0009 0.7890 0.6776
-2.500 -0.2695 0.01544 0.00895 -0.0007 0.7833 0.6852
-2.250 -0.2414 0.01547 0.00897 -0.0006 0.7789 0.6895
-2.000 -0.2142 0.01553 0.00900 -0.0004 0.7743 0.6949
-1.750 -0.1890 0.01547 0.00887 -0.0004 0.7685 0.7016
-1.500 -0.1607 0.01550 0.00890 -0.0003 0.7642 0.7055
-1.250 -0.1337 0.01552 0.00888 -0.0002 0.7601 0.7109
-1.000 -0.1083 0.01547 0.00880 -0.0002 0.7541 0.7169
-0.750 -0.0803 0.01549 0.00883 -0.0001 0.7497 0.7207
-0.500 -0.0529 0.01548 0.00878 0.0000 0.7462 0.7256
-0.250 -0.0278 0.01547 0.00876 -0.0001 0.7399 0.7317
0.000 0.0000 0.01548 0.00880 0.0000 0.7353 0.7353
0.250 0.0277 0.01547 0.00876 0.0001 0.7317 0.7399
0.500 0.0529 0.01548 0.00878 0.0000 0.7256 0.7462
0.750 0.0803 0.01549 0.00883 0.0001 0.7207 0.7497
1.000 0.1083 0.01547 0.00880 0.0002 0.7169 0.7542
1.250 0.1337 0.01552 0.00888 0.0002 0.7109 0.7601
1.500 0.1607 0.01550 0.00891 0.0003 0.7056 0.7642
1.750 0.1889 0.01547 0.00887 0.0004 0.7016 0.7685
2.000 0.2142 0.01553 0.00900 0.0005 0.6949 0.7743
2.250 0.2413 0.01547 0.00897 0.0006 0.6895 0.7789
2.500 0.2695 0.01544 0.00895 0.0007 0.6852 0.7833
2.750 0.2945 0.01547 0.00908 0.0009 0.6776 0.7890
3.000 0.3225 0.01536 0.00898 0.0010 0.6726 0.7938
3.250 0.3481 0.01539 0.00911 0.0013 0.6654 0.7986
3.500 0.3756 0.01528 0.00902 0.0014 0.6589 0.8044
3.750 0.4020 0.01521 0.00903 0.0017 0.6518 0.8093
4.000 0.4288 0.01511 0.00900 0.0021 0.6444 0.8145
4.250 0.4554 0.01503 0.00895 0.0023 0.6369 0.8210
4.500 0.4823 0.01486 0.00887 0.0027 0.6287 0.8255
4.750 0.5079 0.01476 0.00887 0.0032 0.6192 0.8316
5.000 0.5363 0.01452 0.00862 0.0034 0.6109 0.8378
5.250 0.5606 0.01438 0.00864 0.0042 0.5995 0.8434
5.500 0.5858 0.01423 0.00856 0.0048 0.5876 0.8506
5.750 0.6105 0.01402 0.00845 0.0057 0.5741 0.8565
6.000 0.6348 0.01384 0.00835 0.0065 0.5588 0.8640
6.250 0.6585 0.01368 0.00829 0.0076 0.5418 0.8707
6.500 0.6807 0.01354 0.00820 0.0088 0.5191 0.8792
6.750 0.7006 0.01347 0.00815 0.0105 0.4875 0.8872
7.000 0.7184 0.01356 0.00817 0.0124 0.4483 0.8973
7.250 0.7335 0.01384 0.00834 0.0146 0.3996 0.9078
7.500 0.7444 0.01441 0.00870 0.0173 0.3414 0.9203
7.750 0.7547 0.01526 0.00929 0.0196 0.2799 0.9350
8.000 0.7684 0.01647 0.01018 0.0206 0.2135 0.9514
8.250 0.7860 0.01813 0.01144 0.0200 0.1383 0.9698
8.500 0.8050 0.02047 0.01330 0.0179 0.0767 0.9913
8.750 0.7982 0.02140 0.01411 0.0215 0.0648 1.0000
9.000 0.7987 0.02256 0.01523 0.0243 0.0555 1.0000
9.250 0.7998 0.02402 0.01666 0.0266 0.0494 1.0000
9.500 0.8074 0.02521 0.01786 0.0282 0.0441 1.0000
9.750 0.8088 0.02701 0.01960 0.0302 0.0408 1.0000
10.000 0.8200 0.02821 0.02088 0.0315 0.0379 1.0000
10.250 0.8304 0.02948 0.02216 0.0327 0.0351 1.0000
10.500 0.8405 0.03128 0.02387 0.0342 0.0323 1.0000
10.750 0.8547 0.03244 0.02515 0.0352 0.0304 1.0000
11.000 0.8708 0.03376 0.02655 0.0361 0.0289 1.0000
11.250 0.8874 0.03516 0.02803 0.0370 0.0276 1.0000
11.500 0.9050 0.03668 0.02960 0.0377 0.0266 1.0000
11.750 0.9277 0.03872 0.03167 0.0382 0.0254 1.0000
12.000 0.9473 0.04178 0.03495 0.0388 0.0246 1.0000
12.250 0.9505 0.04369 0.03709 0.0400 0.0241 1.0000
12.500 0.9530 0.04593 0.03957 0.0412 0.0237 1.0000
12.750 0.9513 0.04825 0.04212 0.0422 0.0229 1.0000
13.000 0.9495 0.05124 0.04535 0.0430 0.0229 1.0000
13.250 0.9431 0.05454 0.04889 0.0436 0.0228 1.0000
13.500 0.9331 0.05824 0.05285 0.0439 0.0227 1.0000
13.750 0.9200 0.06231 0.05715 0.0438 0.0228 1.0000
14.000 0.9048 0.06684 0.06191 0.0432 0.0230 1.0000
14.250 0.8856 0.07186 0.06716 0.0420 0.0229 1.0000
14.500 0.8682 0.07710 0.07257 0.0402 0.0233 1.0000
14.750 0.8483 0.08303 0.07868 0.0378 0.0236 1.0000
15.000 0.8249 0.08991 0.08575 0.0343 0.0237 1.0000
15.250 0.8025 0.09732 0.09331 0.0303 0.0240 1.0000
15.500 0.7818 0.10517 0.10128 0.0259 0.0244 1.0000
15.750 0.7589 0.11422 0.11042 0.0210 0.0247 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER E837 HYDROFOIL AIRFOIL (e837-il)