EPPLER E838 HYDROFOIL AIRFOIL (e838-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E838 HYDROFOIL AIRFOIL (e838-il) Reynolds number: 100,000 Max Cl/Cd: 29.34 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e838-il-100000-n5.txt Download as CSV file: xf-e838-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.7093 0.12868 0.12358 -0.0221 1.0000 0.0197
-16.750 -0.7344 0.11843 0.11319 -0.0282 1.0000 0.0193
-16.500 -0.7582 0.10939 0.10395 -0.0335 1.0000 0.0192
-16.250 -0.7806 0.10135 0.09569 -0.0378 1.0000 0.0191
-16.000 -0.7991 0.09454 0.08866 -0.0411 1.0000 0.0191
-15.750 -0.8149 0.08854 0.08244 -0.0436 1.0000 0.0191
-15.500 -0.8285 0.08313 0.07679 -0.0456 1.0000 0.0192
-15.250 -0.8395 0.07826 0.07166 -0.0470 1.0000 0.0194
-15.000 -0.8475 0.07394 0.06709 -0.0479 1.0000 0.0197
-14.750 -0.8515 0.07021 0.06310 -0.0485 1.0000 0.0200
-14.250 -0.8504 0.06387 0.05637 -0.0489 1.0000 0.0211
-14.000 -0.8470 0.06142 0.05390 -0.0491 1.0000 0.0221
-13.750 -0.8419 0.05914 0.05151 -0.0491 1.0000 0.0230
-13.500 -0.8341 0.05695 0.04919 -0.0489 1.0000 0.0240
-13.250 -0.8232 0.05493 0.04701 -0.0485 1.0000 0.0252
-13.000 -0.8098 0.05316 0.04504 -0.0479 1.0000 0.0266
-12.750 -0.7963 0.05152 0.04334 -0.0473 1.0000 0.0279
-12.500 -0.7875 0.04976 0.04156 -0.0469 1.0000 0.0295
-12.250 -0.7782 0.04810 0.03986 -0.0466 1.0000 0.0320
-12.000 -0.7662 0.04666 0.03832 -0.0461 1.0000 0.0342
-11.750 -0.7559 0.04512 0.03673 -0.0453 1.0000 0.0366
-11.500 -0.7488 0.04344 0.03507 -0.0447 1.0000 0.0396
-11.250 -0.7392 0.04197 0.03354 -0.0442 1.0000 0.0438
-11.000 -0.7316 0.04041 0.03196 -0.0434 1.0000 0.0475
-10.750 -0.7251 0.03880 0.03038 -0.0427 1.0000 0.0525
-10.500 -0.7179 0.03730 0.02889 -0.0419 1.0000 0.0591
-10.250 -0.7115 0.03582 0.02742 -0.0411 1.0000 0.0682
-10.000 -0.6954 0.03403 0.02569 -0.0427 0.9449 0.0838
-9.750 -0.6806 0.03219 0.02395 -0.0440 0.9223 0.1100
-9.500 -0.6734 0.03035 0.02229 -0.0438 0.9039 0.1458
-9.250 -0.6721 0.02858 0.02070 -0.0425 0.8884 0.1871
-9.000 -0.6765 0.02677 0.01911 -0.0403 0.8753 0.2346
-8.750 -0.6844 0.02501 0.01763 -0.0373 0.8640 0.2872
-8.500 -0.6913 0.02360 0.01661 -0.0337 0.8539 0.3502
-8.250 -0.6830 0.02338 0.01681 -0.0306 0.8456 0.4282
-8.000 -0.6717 0.02335 0.01684 -0.0280 0.8383 0.4725
-7.750 -0.6708 0.02286 0.01626 -0.0246 0.8303 0.4980
-7.500 -0.6551 0.02318 0.01649 -0.0223 0.8243 0.5187
-7.250 -0.6452 0.02326 0.01644 -0.0194 0.8181 0.5356
-7.000 -0.6302 0.02349 0.01654 -0.0172 0.8122 0.5511
-6.750 -0.6091 0.02399 0.01686 -0.0155 0.8077 0.5649
-6.500 -0.5840 0.02459 0.01735 -0.0146 0.8022 0.5767
-6.250 -0.5665 0.02475 0.01736 -0.0129 0.7972 0.5878
-6.000 -0.5364 0.02527 0.01772 -0.0127 0.7935 0.5949
-5.750 -0.5175 0.02524 0.01756 -0.0115 0.7885 0.6028
-5.500 -0.4885 0.02553 0.01771 -0.0114 0.7840 0.6078
-5.250 -0.4774 0.02505 0.01708 -0.0094 0.7798 0.6162
-5.000 -0.4466 0.02528 0.01719 -0.0097 0.7763 0.6194
-4.750 -0.4398 0.02462 0.01640 -0.0073 0.7710 0.6285
-4.500 -0.4104 0.02474 0.01640 -0.0075 0.7671 0.6313
-4.250 -0.3822 0.02479 0.01633 -0.0076 0.7640 0.6345
-4.000 -0.3648 0.02448 0.01592 -0.0065 0.7597 0.6404
-3.750 -0.3467 0.02417 0.01553 -0.0056 0.7553 0.6455
-3.500 -0.3191 0.02418 0.01544 -0.0057 0.7518 0.6482
-3.250 -0.2953 0.02403 0.01519 -0.0052 0.7488 0.6522
-3.000 -0.2832 0.02353 0.01458 -0.0037 0.7442 0.6590
-2.750 -0.2557 0.02359 0.01461 -0.0038 0.7403 0.6612
-2.500 -0.2296 0.02356 0.01451 -0.0038 0.7370 0.6641
-2.250 -0.2068 0.02337 0.01423 -0.0033 0.7341 0.6685
-2.000 -0.1905 0.02305 0.01383 -0.0022 0.7299 0.6740
-1.750 -0.1642 0.02313 0.01391 -0.0022 0.7258 0.6763
-1.500 -0.1386 0.02312 0.01387 -0.0021 0.7225 0.6793
-1.250 -0.1150 0.02296 0.01365 -0.0018 0.7197 0.6833
-1.000 -0.0964 0.02272 0.01333 -0.0010 0.7161 0.6887
-0.750 -0.0716 0.02286 0.01351 -0.0008 0.7116 0.6910
-0.500 -0.0463 0.02290 0.01354 -0.0007 0.7082 0.6939
-0.250 -0.0217 0.02280 0.01341 -0.0005 0.7054 0.6976
0.000 0.0000 0.02255 0.01308 0.0000 0.7028 0.7028
0.250 0.0217 0.02280 0.01341 0.0005 0.6975 0.7054
0.500 0.0463 0.02290 0.01354 0.0007 0.6939 0.7082
0.750 0.0716 0.02286 0.01351 0.0008 0.6910 0.7117
1.000 0.0964 0.02271 0.01332 0.0010 0.6886 0.7161
1.250 0.1150 0.02296 0.01365 0.0018 0.6833 0.7197
1.500 0.1386 0.02312 0.01387 0.0021 0.6793 0.7225
1.750 0.1642 0.02313 0.01391 0.0022 0.6763 0.7259
2.000 0.1905 0.02305 0.01383 0.0022 0.6740 0.7299
2.250 0.2068 0.02337 0.01423 0.0033 0.6684 0.7341
2.500 0.2296 0.02357 0.01452 0.0038 0.6642 0.7370
2.750 0.2556 0.02360 0.01462 0.0038 0.6612 0.7404
3.000 0.2831 0.02353 0.01459 0.0037 0.6590 0.7443
3.250 0.2953 0.02403 0.01519 0.0052 0.6522 0.7488
3.500 0.3191 0.02419 0.01545 0.0056 0.6482 0.7519
3.750 0.3466 0.02418 0.01553 0.0056 0.6455 0.7554
4.000 0.3650 0.02447 0.01592 0.0065 0.6404 0.7598
4.250 0.3822 0.02479 0.01634 0.0076 0.6345 0.7640
4.500 0.4103 0.02474 0.01640 0.0075 0.6314 0.7672
4.750 0.4379 0.02470 0.01648 0.0076 0.6281 0.7711
5.000 0.4466 0.02529 0.01719 0.0097 0.6194 0.7764
5.250 0.4774 0.02505 0.01707 0.0094 0.6162 0.7799
5.500 0.4886 0.02552 0.01771 0.0114 0.6078 0.7841
5.750 0.5175 0.02524 0.01757 0.0115 0.6028 0.7886
6.000 0.5366 0.02526 0.01772 0.0126 0.5950 0.7936
6.250 0.5665 0.02475 0.01736 0.0129 0.5878 0.7973
6.500 0.5841 0.02459 0.01735 0.0146 0.5767 0.8023
6.750 0.6093 0.02399 0.01686 0.0155 0.5649 0.8077
7.000 0.6305 0.02348 0.01653 0.0171 0.5512 0.8122
7.250 0.6454 0.02325 0.01643 0.0194 0.5355 0.8182
7.500 0.6554 0.02315 0.01646 0.0223 0.5183 0.8244
7.750 0.6707 0.02286 0.01627 0.0246 0.4978 0.8303
8.000 0.6719 0.02335 0.01683 0.0280 0.4723 0.8384
8.250 0.6836 0.02335 0.01677 0.0306 0.4275 0.8457
8.500 0.6914 0.02360 0.01660 0.0337 0.3489 0.8540
8.750 0.6846 0.02501 0.01762 0.0372 0.2867 0.8641
9.000 0.6766 0.02677 0.01911 0.0402 0.2338 0.8754
9.250 0.6725 0.02857 0.02069 0.0425 0.1867 0.8886
9.500 0.6734 0.03039 0.02230 0.0438 0.1439 0.9041
9.750 0.6811 0.03219 0.02394 0.0438 0.1095 0.9225
10.000 0.6964 0.03401 0.02567 0.0425 0.0838 0.9452
10.250 0.7122 0.03581 0.02741 0.0410 0.0679 1.0000
10.500 0.7184 0.03730 0.02888 0.0418 0.0588 1.0000
10.750 0.7258 0.03879 0.03036 0.0426 0.0519 1.0000
11.000 0.7323 0.04039 0.03194 0.0433 0.0475 1.0000
11.250 0.7400 0.04196 0.03353 0.0441 0.0439 1.0000
11.500 0.7497 0.04342 0.03504 0.0447 0.0397 1.0000
11.750 0.7573 0.04507 0.03667 0.0452 0.0368 1.0000
12.000 0.7673 0.04662 0.03826 0.0459 0.0344 1.0000
12.250 0.7794 0.04807 0.03982 0.0465 0.0320 1.0000
12.500 0.7884 0.04973 0.04152 0.0468 0.0294 1.0000
12.750 0.7972 0.05152 0.04332 0.0472 0.0278 1.0000
13.000 0.8108 0.05316 0.04506 0.0478 0.0264 1.0000
13.250 0.8247 0.05487 0.04693 0.0484 0.0254 1.0000
13.500 0.8364 0.05686 0.04909 0.0488 0.0243 1.0000
13.750 0.8443 0.05907 0.05145 0.0490 0.0232 1.0000
14.000 0.8489 0.06141 0.05389 0.0490 0.0222 1.0000
14.250 0.8528 0.06386 0.05639 0.0488 0.0213 1.0000
14.500 0.8541 0.06679 0.05942 0.0487 0.0204 1.0000
14.750 0.8550 0.06997 0.06283 0.0484 0.0202 1.0000
15.000 0.8486 0.07394 0.06708 0.0478 0.0197 1.0000
15.250 0.8407 0.07828 0.07168 0.0468 0.0194 1.0000
15.500 0.8308 0.08298 0.07662 0.0455 0.0193 1.0000
15.750 0.8154 0.08864 0.08254 0.0434 0.0190 1.0000
16.000 0.8020 0.09426 0.08837 0.0411 0.0192 1.0000
16.250 0.7816 0.10140 0.09574 0.0376 0.0191 1.0000
16.500 0.7610 0.10909 0.10364 0.0335 0.0192 1.0000
16.750 0.7347 0.11868 0.11344 0.0279 0.0193 1.0000
17.000 0.7092 0.12908 0.12399 0.0217 0.0197 1.0000
17.250 0.6821 0.14111 0.13611 0.0148 0.0201 1.0000
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